Tiltrotor Test Rig Wind-Tunnel Test Data Catalog

NASA/TM − 20240008170

Tiltrotor Test Rig Wind-Tunnel Test Data

Catalog

C. W. Acree, Jr.

Ames Research Center, Moffett Field, California December 2024

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NASA/TM − 20240008170

Tiltrotor Test Rig Wind-Tunnel Test Data

Catalog

C. W. Acree, Jr.

Ames Research Center, Moffett Field, California National Aeronautics and Space Administration Ames Research Center Moffett Field, CA 94035-1000 December 2024 Available from: NASA STI Program / Mail Stop 050 NASA Langley Research Center Hampton, VA 23681-2199

Table of Contents

List of Tables

tip

List of Figures

Fig. 3. The NFAC configured for normal 40x80 operations, with the TTR at 0-deg yaw angle ..15 Fig. 4. The NFAC configured for reverse-flow operations, with the TTR at 180-deg yaw angle.15 Nomenclature BDAS Basic Data Acquisition System BVI Blade-Vortex Interaction DCMS Drive Control Monitoring System DDAS Dynamic Data Acquisition System CCW Counter-Clockwise CTOS 𝐶 / 𝜎 !

CW Clockwise NFAC National Full-Scale Aerodynamics Complex RDMS Rotor Database Management System SDAS Steady Data Acquisition System SOF Safety of Flight SOFDAS Safety of Flight Data Acquisition System TTR Tiltrotor Test Rig VS Vane Set 40x80 NFAC 40- by 80-ft Wind Tunnel A Rotor disk area c Rotor chord (thrust weighted) # ⁄ C Thrust coefficient, 𝑇 𝜌𝐴 𝑉 T " D Drag M Tip Mach number tip N Number of blades P Rotor power P Rotor induced power i # q Dynamic pressure, ½ 𝜌 𝑉 R Rotor radius T Rotor thrust V Wind tunnel airspeed V´ Glauert-corrected airspeed V Rotor tip speed t η Propulsive efficiency, 𝑇𝑉 / 𝑃 = 𝜇 𝐶 / 𝐶 ! $ 𝜇 Advance ratio, 𝑉 / 𝑉 " Ω Rotor rotation rate 𝜌 Atmospheric density 𝜎 Rotor solidity, Nc / 𝜋 R ; standard deviation Rotor Balance and Shaft Loads AF Axial Force NF Normal Force SF Side Force PM Pitching Moment RM Rolling Moment YM Yaw Moment B3, B4 Loads from B3 & B4 calibrations _SH Shaft Loads _A, _B Primary & backup strain gages Test Point Data Type CAL R-cal data point Cont Continuously recorded point REC Recorded data point SIM Simulated rotation STATIC Non-rotating reference condition ZER Calibration zero point

Summary

The Tiltrotor Test Rig (TTR) is a large-scale proprotor test system for the National Full-Scale Aerodynamics Complex (NFAC). The first wind-tunnel entry was completed in November 2018 with a modern, 26-ft diameter proprotor. The rotor tested was the Bell Model 699, an AW609 rotor modified specifically for wind-tunnel testing. The primary purpose was to complete the development of the TTR, including systems integration with the NFAC. Testing included axial flow up to 273 knots, conversion mode from 30 to 100 deg nacelle angle, and hover/vertical climb conditions. Additional testing included aerodynamic tares, motor tests, thermal tests, modal vibration tests, and other checkout activities. This report lists the test conditions achieved and the types of data acquired and saved in the database.

Introduction

The Tiltrotor Test Rig (TTR) is designed to test large-scale proprotors at high-speed axial flight conditions, tiltrotor conversion mode, and helicopter mode. The TTR was jointly developed by NASA, the U. S. Army and the U. S. Air Force and constructed by Bell Textron. The first entry of the TTR into the NFAC was completed in November 2018. It was considered a checkout test focused on operational safety and efficiency, but the opportunity was used to collect rotor performance, loads, and acoustics data for research. The checkout test used the Bell Model 699 rotor (Figure 1), which was built specifically for NASA by Bell and derived from the right-hand rotor of the Leonardo AW609.

Fig. 1. TTR/699 installed in the NFAC 40- by 80-ft test section, 45-deg yaw.

Dimensions and capabilities of the TTR/699 are summarized in Reference 1, which also includes a description of the NFAC data system. Rotor performance measurements taken during the first entry are given in References 1-3, which have been published as NASA Technical Memoranda (TMs). NASA TMs generally contain more recent and extensive results than conference papers and are available online. References 1-3 are accordingly recommended as the preferred sources of information on the TTR.

Other useful documents were published as conference papers. Development of the TTR/699 is described in Reference 4, and the test program is described in References 5-6. Acoustics measurements are described in Reference 7. References 8-10 document analytical studies of TTR/699 aeroelastic stability, performance, and airloads. Reference 11 presents a correlation study of performance and loads data and predictions.

Calibration of the TTR rotor balance system is described in Reference 12, and ground vibration testing is described in Reference 13. The NFAC data system is described in Reference 14.

Equations for most TTR/699 derived parameters are given in Reference 15.

After acquisition by the NFAC data system, research data are stored in the Rotor Database Management System (RDMS). The present catalog lists all test conditions and data parameters in the database. The section Test Conditions includes summary tables of wind-tunnel runs and NFAC configurations, and tables of data runs organized by category: aerodynamic tares, hover/vertical climb, conversion mode, airplane mode, and dedicated acoustics measurements.

A comprehensive table of all runs and test points is included. The user may profit from examining the summary tables first, followed by the full table, before accessing the database.

The section Instrumentation and Derived Parameters has tables of all types of data stored in the database, organized by data type: operating conditions, rotor balance, rotor coefficients, wall pressures, etc. Note that some data items appear in more than one table.

Test Conditions

For the tables given here, nominal rotor operating conditions are: Helicopter mode: 569 rpm = 775 ft/sec, M = 0.693 tip Airplane mode: 478 rpm = 651 ft/sec, M = 0.580 tip Table 1 summarizes the TTR wind tunnel runs. The RDMS column indicates whether data for that run are stored in the database: Y = Yes. Y+A indicates that acoustics data are also stored. In a few cases, run numbers were assigned but the run was cancelled or aborted before useful data were acquired. Several runs are included where it was convenient to process calibration and weight-check data through the NFAC data system. Yaw and q values are nominal: not all test conditions were achieved each run.

More detailed tables summarize the runs by operating condition and type of data acquired. Table 2 lists the spinner tare runs (rotor off), including weight tares and background noise measurements. See also Reference 2. Figure 2 graphically shows the test conditions for a subset of the tare data taken at coarse and fine increments of yaw angle and consistent values of dynamic pressure. These data are the most important for determining TTR aerodynamic tares.

Table 1. TTR/699 Summary Run Log No.

Run Date RDMS Description Notes Points Systems Checks and Aerodynamic Tares: Rotor and Hub Off, Spinner and Fairings Installed 1 4/28/17 29 Y Yaw check, 0 airspeed, weight tares 2 4/28/17 19 Y Heating run, 0 airspeed bad rpm data 3 5/1/17 77 Y Heating run, 0 airspeed MG set trip 4 5/1/17 34 Y Spin only run, 0 airspeed, hysteresis check 5 5/1/17 37 Y Heating run, 0 airspeed 6 5/3/17 39 Y Heating run, 0 airspeed 7 5/3/17 19 Y Heating run, 0 airspeed 8 5/3/17 9 N q sweep, 478 rpm, 0 deg yaw tunnel trip 9 5/4/17 39 Y Heating run, 0 airspeed 10 5/4/17 23 Y+A q sweep, 478 rpm, 0 deg yaw tunnel trip 11 5/4/17 26 Y Heating run, 0 airspeed 12 5/4/17 20 Y+A q sweep, 478 rpm, 0 deg yaw tunnel trip 13 5/8/17 28 Y Heating run, 0 airspeed 14 5/8/17 30 Y+A q sweep, 478 rpm, 0 deg yaw 15 5/8/17 30 Y Heating run 16 5/8/17 24 Y+A q sweep, 478 rpm, 90 deg yaw 17 5/10/17 39 Y Heating run 18 5/10/17 23 Y+A q sweep, 569 rpm, 15 deg yaw 19 5/11/17 41 Y Heating run 20 5/11/17 8 N 30 deg yaw tunnel trip 21 5/11/17 29 Y Heating run 22 5/11/17 176 Y+A q sweeps, 569 rpm, 30 to 100 deg yaw 23 5/12/17 8 N 90 deg yaw tunnel trip 24 5/12/17 41 Y Heating run 25 5/12/17 15 Y Yaw sweep, 569 rpm, q = 12 psf 26 5/12/17 32 Y Acoustic/heating run, 90 deg yaw 27 5/12/17 19 Y q sweep, 569 rpm, 90 deg yaw Table 1. TTR/699 Summary Run Log (continued) No.

Run Date RDMS Description Notes Points 28 5/12/17 30 Y Yaw sweeps, 569 rpm, q = 12 psf 29 5/17/17 4 N Acoustic cal 30 5/17/17 36 Y Heating run 31 5/17/17 43 Y+A Yaw sweep, 569 rpm, q = 36 psf 32 5/17/17 28 Y Heating run 33 5/17/17 60 Y+A Yaw sweeps, 569 and 0 rpm, q = 75 psf Rotor Installation, Track and Balance 34 5/22/17 20 N Buildup: begin blade installation; -45 deg yaw for blade installation blades installed 22-23 May 35 5/23/17 — N No run 36 5/23/17 15 Y Blade installation; -45 deg yaw 37 5/24/17 4 N Acoustic cal 38 6/1/17 15 N Gage offset coefficient terms 25 deg coll 39 6/1/17 34 N Gravity effects 25 deg coll 40 6/1/17 18 N Gravity effects 5 deg coll 41 6/2/17 29 N Control actuator position calibration 42 6/2/17 17 N Control actuator position check 43 6/5/17 3 N Discard run 44 6/6/17 13 N Control system check 45 6/6/17 22 N Control system validation 46 6/6/17 7 N Control system check 47 6/9/17 30 Y Hover balancing run – nominal blade tip weights balance heater off (?)

48 8/17/17 5 N Hover balancing run – new blade tip weights (no rotation), hub flap check blades reinstalled 27 July 49 8/21/17 38 Y Hover balancing run – new blade tip weights limited operations during NFAC shutdown 50 8/22/17 19 Y Hover balancing run – new blade tip weights 51 8/22/17 16 Y Hover balancing run – run 50 tip weights, removed rotating scissor weight 52 9/6/17 40 N Blade bending offsets at 15 deg collective Table 1. TTR/699 Summary Run Log (continued) No.

Run Date RDMS Description Notes Points Checkout Runs after NFAC Repairs 53 — 0 N No run 54 3/19/18 0 N Aborted run 55 3/19/18 17 Y Hover Balancing run – no rotating counterweight, swashplate balancing plate installed 56 3/19/18 27 Y Hover balancing run – green weight 233.6 g, white weight 177.7 g 57 3/19/18 25 Y Hover balancing run – green weight 177.8 g, white weight 177.7 g 58 3/20/18 27 Y Hover balancing run – green weight 123.2 g, white weight 177.7 g Wind-Off Thrust Sweeps 59 3/26/18 41 Y Thrust checkout: 0 deg yaw, rpm sweep; Vane Set 3 open, VS 4, 6 & 7 closed high loads 60 3/26/18 26 Y Thrust checkout: 0 deg yaw, 569 rpm, Vane Set 3 open, VS 4, 6 & 7 closed hit SOF limits 61 3/27/18 29 Y Thrust checkout: 0 deg yaw, 569 rpm, Vane Set 3 open, VS 4, 6 & 7 closed hit SOF limits 62 3/27/18 29 Y Thrust checkout: 180 deg yaw, 569 rpm, Vane Set 3 open, VS 4, 6 & 7 closed 63 3/27/18 29 Y Thrust checkout: 180 deg yaw, 569 rpm, Vane Set 3 closed, VS 4, 6 & 7 open Blades-Off Calibrations and Swashplate Tares 64 5/14/18 4 N Acoustic cal blades removed for NFAC IST 65 5/15/18 5 N Acoustic cal take 2 66 5/30/18 10 N Acoustic cal 67 6/21/18 6 N Acoustic cal 68 7/10/18 13 N Acoustic cal 69 7/12/18 27 N Acoustic cal 70 7/23/18 4 N Acoustic cal 71 7/26/18 31 Y Swashplate balance tare, spinner fairing and nose cone installed, rpm sweep 72 7/26/18 79 Y Swashplate balance tare, spinner fairing and nose cone installed, collective sweep 73 8/6/18 9 N Acoustic cal blades installed 1-2 Aug Table 1. TTR/699 Summary Run Log (continued) No.

Run Date RDMS Description Notes Points Blades-On Testing 74 8/8/18 52 Y+A Post-IST hover checkout, rpm & collective sweeps, 0 deg yaw, wind off 75 8/13/18 58 Y+A Airplane forward flight, 0 deg yaw, 478 RPM, 60, 90 knots 76 8/13/18 41 Y Airplane forward flight, 0 deg yaw, 478 RPM, 120, 150 knots; no cooling water poor data quality?

77 8/14/18 50 Y+A Airplane forward flight, 0 deg yaw, 478 RPM, 150, 180, 210 knots tunnel trip 78 8/16/18 27 Y Motor current checkout, thrust sweep, 0 deg yaw, 478 rpm, wind off 79 8/16/18 34 Y Static rotor control rate check 80 8/16/18 53 Y+A Airplane forward flight, operator training, 0 deg yaw, 478 RPM, 60, 150, 210 knots 81 8/17/18 43 Y+A Airplane forward flight, operator training, 0 deg yaw, 478 RPM, 240-270 knots hit fan drive BMS limits 82 8/22/18 8 N Acoustic cal 83 8/22/18 17 Y Helicopter forward flight, 90 deg - aborted 84 8/23/18 2 N Acoustic cal 85 8/27/18 42 Y+A Helicopter forward flight, 90 deg, 57, 80 knots 86 8/28/18 42 Y+A Conversion forward flight, thrust sweeps, 90, 75 deg yaw, 57 knots 87 8/29/18 71 Y+A Conversion forward flight, thrust sweeps, 75 deg yaw, 57, 70, 81, 92 knots 88 8/30/18 85 Y+A Conversion forward flight, thrust sweeps, 75 deg yaw, 104, 115 knots 89 8/30/18 56 Y+A Conversion forward flight, thrust sweeps, 60 deg yaw, 70, 81 knots 90 8/31/18 83 Y+A Conversion forward flight, thrust sweeps, 60, 45 deg yaw, 91, 103, 115, 126 knots 91 9/4/18 40 Y+A Conversion forward flight, thrust sweeps, 45 deg yaw, 57, 103 & 115 knots 92 9/5/18 14 Y Conversion forward flight, thrust sweeps, 90 deg yaw - RCC issue recirculation, aborted 93 9/5/18 81 Y+A Conversion forward flight, thrust sweeps, 45, 30 deg yaw, 104, 115, 127, 138 knots 94 9/6/18 65 Y+A Conversion forward flight, thrust sweeps, 30, 80 deg yaw, 57, 137, 149, 160 knots 95 9/6/18 26 Y+A Conversion forward flight, thrust sweeps, 90 deg yaw, 57 knots 96 9/19/18 7 N Acoustic cal 97 10/17/18 4 N Acoustic cal 98 11/5/18 5 N Acoustic cal 99 11/6/18 23 Y+A Motor checkout (both fwd motors); NFAC configuration effects new trunnion etc. in rotating scissors 100 11/6/18 20 Y+A Motor checkout (port motor disconnected, running motor 5 only); NFAC config. effects Table 1. TTR/699 Summary Run Log (concluded) No.

Run Date RDMS Description Notes Points 101 11/7/18 33 Y+A NFAC configuration effects, thrust sweep, 0 deg yaw, 569 rpm 102 11/7/18 52 Y+A NFAC configuration effects, thrust sweeps, 0 deg yaw, 569 & 478 rpm 103 11/7/18 25 Y+A NFAC configuration effects, thrust sweep, 0 deg yaw, 569 rpm 104 11/8/18 48 Y+A Airplane forward flight, thrust sweep, 478 rpm, 120 knots 105 11/8/18 59 Y+A Airplane forward flight, thrust sweeps, 569 rpm, 61, 72, 107, 143 knots 106 11/9/18 36 Y+A Helicopter forward flight, thrust sweep, 90 deg yaw, 57 knots 107 11/9/18 46 Y+A Acoustic BVI helicopter mode testing, yaw sweep & thrust sweep, 57 knots 108 11/13/18 37 Y+A Airplane forward flight, 0 yaw, 569 rpm, 176, 212 knots 109 11/13/18 62 Y+A Helicopter forward flight, thrust sweeps, 569 rpm, 80, 85, 95, 100 deg yaw, 57 knots 110 11/14/18 58 Y+A Motor checkout (both aft motors) & thrust sweeps, 478 & 569 rpm, wind off; NFAC config. effects Blades Off, Hub On (Spindles Exposed) 111 11/16/18 30 Y+A Aerotare, yaw sweep, q = 75 psf, blades off, hub taped; both AFT motors terminated due to loose cowling Table 2. Aerodynamic Tare Test Points RPM Yaw Angle q , lb/ft Run Notes 478 0 0-223 10,12,14 Only Run 14 is complete.

569 15 0-75 18 q sweeps at fixed yaw 569 30,45,60,75 0-75 22 569 90 0-75 16 553 90 16,21,28 26 acoustics checks 569 90 0-36 27 acoustics 569 0-90 0 25 weight & acoustics checks 0-90 12 28 repeated yaw sweep 569 80-100 16,22,29,36 22 2-deg yaw increments 569 0-100 36 31 2-deg increments 65-100 569 0-100 75 33 2-deg increments 65-100 0 0-100 75 33 acoustics checks Dynamic Pressure, lb/ft 100 80 60 40 20 0 T-frame Yaw Angle, deg Fig. 2. Aerodynamic Tare Test Points NFAC tests where only the rotor is powered are frequently referred to as hover tests, simply because the drive fans are not used and airspeed is not controlled. For rotors installed with the shaft axis parallel to the flow direction, the resulting test conditions are actually vertical climb with variable tunnel airspeed (rate of climb) because the rotor’s induced velocity causes flow around the closed tunnel circuit.

Table 3 summarizes the hover/vertical climb runs. See also Reference 2. Figures 3 and 4 illustrate the wind tunnel configurations. The rotor is pointing in the upstream direction at 0-deg yaw and in the reverse direction at 180-deg yaw. Most data were taken at M = 0.693 (569 rpm). Runs 102 tip and 110 included data at both M = 0.693 and M = 0.583 (479 rpm). Run 78 was a motor test at tip tip fixed shaft speed (478 rpm), so M does not match perfectly with Runs 102 and 110. For Run 59 tip only, the personnel access door was open. The Air Exchange was always open. Not all runs include full thrust sweeps.

For completeness, the table includes a few runs that yielded only limited research data. Run 59 was a procedural checkout run (the last track and balance run). Runs 99 and 100 were motor tests with very few data points.

Table 3. Hover/Vertical Climb NFAC Configurations Yaw angle, Run VS 3 VS 4 VS 6/7 M Notes tip deg 59 0 open closed closed .684 high loads 60 0 open closed closed .684 high loads 61 0 open closed closed .684 62 180 open closed closed .684 63 180 closed open open .684 78 0 open closed closed .583 motor test 99 0 open closed open .684 motor test 100 0 open closed open .684 motor test 101 0 open open open .684 a 102 0 4/8 open open open .583, .684 a 103 0 open open .684 2/8 open 110 0 open closed open .583, .684 a N/A closed not possible 4/8 open a VS 3 has 8 panels, so specified as n/8 open.

Atmospheric Inlet 80x120 Test Section Air Drive Vane Set 6, Exchange Deflected Fans Exhaust Vane Set 4, Closed Vane Set 3, Fully Open Vane Set 7, Air Exchange Inlet Closed 40x80 Test Section TTR 2X Scale Fig. 3. The NFAC configured for normal 40x80 operations, with the TTR at 0-deg yaw angle.

Fig. 4. The NFAC configured for reverse-flow operations, with the TTR at 180-deg yaw angle.

Table 4 summarizes the conversion-mode test points. See also Reference 1. The information in Table 4 is graphically shown in Figure 5.

Table 4. Conversion Mode Thrust Sweeps ( M tip = 0.684) Yaw angle, VKTS Run 𝜇 deg 100 57.4 0.125 109 95 57.4 0.125 109 90 57.4 0.125 95 85 57.4 0.125 109 80 57.4 0.125 94 90 56.6 0.125 85 75 56.6 0.125 86 75 69.4 0.151 87 75 80.8 0.176 87 75 92.4 0.201 87 75 104 0.226 88 75 115 0.250 88 60 69 0.150 89 60 81 0.176 89 60 91 0.198 90 60 103 0.224 90 60 114 0.248 90 60 126 0.274 90 45 92 0.200 90 45 103 0.225 91 45 115 0.250 91 45 126 0.275 93 45 138 0.300 93 30 104 0.225 93 30 115 0.250 93 30 127 0.275 93 30 137 0.300 94 30 148 0.325 94 30 160 0.350 94 Fig. 5. Nominal conversion-mode envelope and test conditions.

Table 5 summarizes the airplane-mode test points. See also Reference 1.

Table 5. Airplane Mode Thrust Sweeps (Yaw = 0 deg) M VKTS Runs tip 𝜇 0.583 61 0.156 75, 80 91 0.233 75 122 0.312 76, 104 152 0.391 76, 77, 80 182 0.468 77 214 0.544 77, 80 243 0.622 81 264 0.674 81 0.684 61 0.133 105 71 0.156 105 107 0.233 105 143 0.311 105 176 0.391 108 211 0.468 108 Table 6 summarizes the Blade-Vortex Interaction (BVI) test points for acoustics measurements.

See also Reference 7. Background noise measurements were included in the aerodynamic tare runs, and acoustics data were taken at many other non-BVI conditions, as denoted in Table 1.

Table 6. Acoustics BVI Test Points C / 𝜎 = 0.075, 𝜇 = 0.125 T All Run 107 Yaw range Increment 80-86 deg 2 deg 88-100 deg 1 deg Table 7 is a detailed run log, with all data points for runs for which data were acquired and stored in the RDMS database. The table is a heavily redacted version of the NFAC run log. Most of the omitted runs, notably 37-46, were instrumentation checks and calibrations. Initialization points such as instrumentation zeros and R-cals are not normally stored in the database, but all are listed here. “Static” points are non-rotating reference conditions; they are not consistently labeled in the original NFAC run log.

The NFAC data system requires a 1/rev pulse to trigger data acquisition. At zero rotor speed, a dummy trigger is applied which results in a rotor speed reading of 499.095 rpm. Dummy rpm readings are denoted “SIM” in the run log as a reminder that the values are not physical data.

Exactly which parameters are listed depends upon the purpose of the run and point. Airspeed is not always given for wind-off conditions. For hover/vertical climb runs (Table 3), the NFAC fan drives were not used and the airspeed is that generated by the 699 rotor.

Tunnel speed is given as dynamic pressure for rotor-off aerodynamic tare runs, but as airspeed (knots) for rotor-on runs. Nondimensional coefficients— M , C / 𝜎 , and 𝜇 —are given where the tip T rotor was trimmed to those values. Standard practice was to set reference points on shaft speed (rpm), tunnel speed (knots), and collective (deg), then switch to coefficients for trim where appropriate.

Motor current is not stored in the RDMS database, but for three runs—99, 100, and 110—the values were recorded by hand in the NFAC run log and are included here.

Table 7. TTR/699 Run Log Run TR092RN001 4/28/2017 Yaw check, 0 airspeed, weight tares Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL/AB ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL BAD ZERO/RCAL combination ZER 5 0 0 0 ZERO CAL 6 0 0 0 RCAL/AB ZER 7 0 0 0 ZERO CAL 8 0 0 0 RCAL REC 9 0 0 0 Static w/ RCAL REC 10 0 0 0 STATIC REC 11 0 0 0 REC 12 15 0 0 REC 13 30 0 0 REC 14 45 0 0 REC 15 60 0 0 REC 16 75 0 0 REC 17 90 0 0 REC 18 100 0 0 REC 19 90 0 0 REC 20 75 0 0 REC 21 60 0 0 REC 22 45 0 0 REC 23 30 0 0 REC 24 15 0 0 REC 25 0 0 0 Static Point REC 26 0 0 0 STATIC REC 27 0 0 0 Static w/ RCAL ZER 28 0 0 0 ZERO CAL 29 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN002 4/28/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL/AB ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL REC 5 0 0 0 Static w/ RCAL REC 6 0 0 0 STATIC REC 7 0 0 0 bad point?

REC 8 0 200 0 Not getting correct RPM from model REC 9 0 200 0 Not getting correct RPM from model REC 10 0 200 0 Not getting correct RPM from model REC 11 0 400 0 No Pulse - repeating point REC 12 0 400 0 REC 13 0 569 0 REC 14 0 200 0 REC 15 0 0 0 Static Point REC 16 0 0 0 STATIC REC 17 0 0 0 Static w/ RCAL ZER 18 0 0 0 ZERO CAL 19 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN003 5/1/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL/AB ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 0 200 0 no link to acoustics REC 7 0 200 0 repeating pt/Acoustic issues REC 8 0 400 0 REC 9 0 569 0 Cont 10-21 0 569 0 Hold for 60 min or heat stabilizes, periodic data every min 0 PT 21 is bad - MG set tripped in middle of point Cont 22-73 0 569 0 Repeat periodic data - SOFDAS activated REC 74 0 200 0 REC 75 0 0 0 STATIC ZER 76 0 0 0 ZERO CAL 77 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN004 5/1/2017 Spin only run, 0 airspeed, hysteresis check Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL REC 5 0 0 0 Static w/ RCAL REC 6 0 0 0 STATIC REC 7 0 60 0 RPM sweep, 0 airspeed/Simulated RPM set at 500 REC 8 0 60 0 RPM sweep, 0 airspeed/Repeat pt REC 9 0 100 0 REC 10 0 150 0 REC 11 0 200 0 REC 12 0 250 0 REC 13 0 300 0 REC 14 0 350 0 REC 15 0 400 0 REC 16 0 450 0 REC 17 0 478 0 REC 18 0 525 0 REC 19 0 569 0 REC 20 0 525 0 hysteresis check: reverse RPM sweep REC 21 0 478 0 REC 22 0 450 0 REC 23 0 400 0 REC 24 0 350 0 REC 25 0 300 0 REC 26 0 250 0 REC 27 0 200 0 TS kept 128 Rot after setting at 32 REC 28 0 150 0 REC 29 0 100 0 REC 30 0 60 0 REC 31 0 0 0 STATIC/ 16 sec sdas point REC 32 0 0 0 STATIC/ 16 sec sdas point/repeated static ZER 33 0 0 0 ZERO CAL 34 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN005 5/1/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL/AB ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 0 200 0 REC 7 0 400 0 REC 8 0 569 0 Single point Cont 9 - 33 0 569 0 Continuous 1 min delay (569 Rots) SDAS pt 33 is bad REC 34 0 200 0 Post point - causing trip REC 35 0 0 0 STATIC ZER 36 0 0 0 ZERO CAL 37 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN006 5/03/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL/AB ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC/started SOF/ Restart 1 per rev issues with rotor REC 6 0 200 0 REC 7 0 400 0 Point did not post process REC 8 0 400 0 REC 9 0 569 0 REC 10-20 0 569 0 Hold for 60 min or heat stabilizes, periodic data every min 0 0 Multiple Points did not post process: error opening BDAS .rstat file REC 21 0 569 0 Multiple Points did not post process: error opening BDAS .rstat file REC 22 0 569 0 Multiple Points did not post process: error opening BDAS .rstat file Cont 23-33 0 569 0 Hold for 60 min or heat stabilizes, periodic data every min 0 0 Multiple Points did not post process: error opening BDAS .rstat file REC 34 0 400 0 Multiple Points did not post process: error opening BDAS .rstat file REC 35 0 400 0 REC 36 0 200 0 REC 37 0 0 0 STATIC ZER 38 0 0 0 ZERO CAL 39 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN007 5/3/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO CAL 4 0 0 0 RCAL ZER 5 0 0 0 ZERO CAL 6 0 0 0 RCAL/proceed per DAN REC 7 0 0 0 STATIC REC 8 0 200 0 Cont 9 - 15 0 478 0 Continuous data points REC 16 0 200 0 REC 17 0 0 0 STATIC ZER 18 0 0 0 ZERO CAL 19 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN009 5/4/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor VKTS Notes Type Point deg RPM ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 0 200 0 Point was too long in SDAS - captured RPM acceleration to 569 REC 7 0 400 0 REC 8 0 569 0 Cont 9-13 0 569 0 Hold for 60 min or heat stabilizes, periodic data every min Cont 14-34 0 478 0 Hold for 60 min or heat stabilizes, periodic data every min Cont 32-35 0 478 0 32-35 BDAS was taken as single pt catch-up points REC 36 0 200 0 REC 37 0 0 0 Static Point ZER 38 0 0 0 ZERO CAL 39 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN010 5/4/2017 q sweep, 478 rpm, 0 - deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL ZER 5 0 0 0 ZERO CAL 6 0 0 0 RCAL ZER 7 0 0 0 ZERO (AB) CAL 8 0 0 0 RCAL REC 9 0 0 0 STATIC REC 10 0 478 0 Reference point REC 11 0 478 12 did not send pulse to acoustic REC 12 0 478 12 Repeat pt / VPM_Angle 7.01 REC 13 0 478 30 REC 14 0 478 30 repeat pt REC 15 0 478 30 repeat pt REC 16 0 478 60 REC 17 0 478 90 REC 18 0 478 120 REC 19 0 478 150 REC 20 0 478 180 SOF 19 Tunnel Estop REC 21 0 0 0 STATIC ZER 22 0 0 0 ZERO CAL 23 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN011 5/4/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 0 200 0 REC 7 0 400 0 REC 8 0 478 0 Cont 9-22 0 478 0 Hold for 60 min or heat stabilizes, periodic data every min Taking 2 single BDAS points to catch up REC 23 0 200 0 REC 24 0 0 0 Static Point ZER 25 0 0 0 ZERO CAL 26 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN012 5/4/2017 q sweep, 478 rpm, 0 - deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 0 478 0 Reference point REC 7 0 478 12 REC 8 0 478 30 REC 9 0 478 60 REC 10 0 478 90 No angle entered manually REC 11 0 478 90 Repeat pt REC 12 0 478 120 REC 13 0 478 150 REC 14 0 478 180 REC 15 0 478 210 REC 16 0 478 203 q was fluctuating/Tunnel trip REC 17 0 478 0 Reference point REC 18 0 0 0 STATIC ZER 19 0 0 0 ZERO CAL 20 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN013 5/8/2017 Heating run, 0 airspeed Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 0 200 0 REC 7 0 400 0 REC 8 0 478 0 Cont 9-24 0 478 0 Hold for 60 min or heat stabilizes, periodic data every min REC 25 0 200 0 REC 26 0 0 0 Static Point ZER 27 0 0 0 ZERO CAL 28 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN014 5/8/2017 q sweep, 478 rpm, 0 - deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 478 0 RCAL REC 5 0 478 0 STATIC REC 6 0 478 0 Reference point REC 7 0 478 12 REC 8 0 478 30 REC 9 0 478 60 REC 10 0 478 90 REC 11 0 478 120 REC 12 0 478 150 REC 13 0 478 180 REC 14 0 478 210 REC 15 0 478 223 REC 16 0 478 210 REC 17 0 478 180 REC 18 0 478 150 REC 19 0 478 120 REC 20 0 478 90 REC 21 0 478 60 REC 22 0 478 60 Acoustics did not get signal/repeating pt REC 23 0 478 30 REC 24 0 478 12 REC 25 0 478 12 Acoustics did not get signal/repeating pt REC 26 0 0 0 Reference point REC 27 0 0 0 Reference point/Manual inputs still had value/repeat pt REC 28 0 0 0 STATIC ZER 29 0 0 0 ZERO CAL 30 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN015 5/8/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL ZER 5 0 0 0 ZERO (AB) CAL 6 0 0 0 RCAL REC 7 0 0 0 STATIC REC 8 90 200 0 REC 9 90 400 0 REC 10 90 569 0 Cont 11 - 26 90 569 0 Hold for 60 min or heat stabilizes, periodic data every min REC 27 90 200 0 REC 28 0 0 0 Static Point ZER 29 0 0 0 ZERO CAL 30 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN016 5/8/2017 q sweep, 478 rpm, 90-deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 90 0 0 ZERO CAL 2 90 0 0 RCAL REC 3 90 0 0 STATIC REC 4 90 569 0 Reference point REC 5 90 569 0 Wind on Ref REC 6 90 569 0 REC 7 90 569 12 REC 8 90 569 25 REC 9 90 569 35 REC 10 90 569 45 REC 11 90 569 55 strut limit is 75 psf REC 12 90 569 65 hysteresis check: reverse q sweep REC 13 90 569 75 REC 14 90 569 65 REC 15 90 569 55 REC 16 90 569 45 REC 17 90 569 35 REC 18 90 569 25 Wind on Ref REC 19 90 569 15 Reference point; skip if proceed immediately to next azimuth REC 20 90 0 12 Static Point REC 21 90 0 0 STATIC ZER 22 90 0 0 STATIC ZER 23 90 0 0 ZERO CAL 24 90 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN017 5/10/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL REC 5 0 0 0 STATIC REC 6 15 200 0 REC 7 15 400 12 REC 8 15 569 25 Cont 9-35 15 569 35 Hold for 60 min or heat stabilizes, periodic data every min REC 36 15 200 45 REC 37 0 0 55 Static Point ZER 38 0 0 65 ZERO CAL 39 0 0 75 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN018 5/10/2017 q sweep, 569 rpm, 15 deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 CAL 2 0 0 0 AB ZER 3 0 0 0 CAL 4 0 0 0 REC 5 0 0 0 STATIC REC 6 15 569 0 Reference point REC 7 15 569 12 Wind on reference point REC 8 15 569 25 REC 9 15 569 35 REC 10 15 569 45 REC 11 15 569 55 REC 12 15 569 65 REC 13 15 569 75 strut limit is 75 psf REC 14 15 569 65 REC 15 15 569 55 REC 16 15 569 45 REC 17 15 569 35 REC 18 15 569 25 REC 19 15 569 12 Wind on reference point REC 20 15 569 0 Reference point REC 21 0 0 0 STATIC ZER 22 0 0 0 ZERO CAL 23 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN019 5/11/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 CAL 2 0 0 0 ZER 3 0 0 0 CAL 4 0 0 0 REC 5 0 0 0 STATIC REC 6 30 200 0 REC 7 30 400 0 REC 8 30 569 0 Cont 9-37 30 569 0 Hold for 60 min or heat stabilizes, periodic data every min REC 38 30 200 0 REC 39 0 0 0 Static Point ZER 40 0 0 0 CAL 41 0 0 0 Table 7. TTR/699 Run Log (continued) Run TR092RN021 5/11/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 CAL 2 0 0 0 AB ZER 3 0 0 0 CAL 4 0 0 0 REC 5 0 0 0 STATIC REC 6 30 200 0 REC 7 30 400 0 REC 8 30 569 0 Cont 9 - 24 30 569 0 Hold for 60 min or heat stabilizes, periodic data every min REC 25 30 200 0 REC 26 0 0 0 Static Point/ SDAS was 16 sec REC 27 0 0 0 Repeat last pt ZER 28 0 0 0 CAL 29 0 0 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN022 5/11/2017 q sweeps, 569 rpm, 30 to 100 deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 30 SIM 0 CAL 2 30 SIM 0 AB ZER 3 30 SIM 0 CAL 4 30 SIM 0 ZER 5 30 SIM 0 CAL 6 30 SIM 0 REC 7 30 SIM 0 STATIC REC 8 30 SIM 0 REC 9 30 SIM 12 REC 10 30 569 12 REC 11 30 569 25 REC 12 30 569 35 REC 13 30 569 45 REC 14 30 569 55 REC 15 30 569 65 REC 16 30 569 75 REC 17 30 569 65 REC 18 30 569 55 REC 19 30 569 45 REC 20 30 569 35 REC 21 30 569 25 REC 22 30 569 12 REC 23 30 SIM 12 RPM was not set to Normal as we came down - bad point REC 24 30 SIM 12 Repeat wind on reference after coming back to condition REC 25 30 SIM 12 Repeat wind on reference after coming back to condition REC 26 45 SIM 12 REC 27 45 569 12 REC 28 45 569 25 REC 29 45 569 35 REC 30 45 569 45 REC 31 45 569 55 REC 32 45 569 65 REC 33 45 569 75 REC 34 45 569 65 REC 35 45 569 55 REC 36 45 569 45 REC 37 45 569 35 REC 38 45 569 25 REC 39 45 569 12 REC 40 45 SIM 12 REC 41 45 SIM 12 Repeat pt per acoustics request REC 42 60 SIM 12 REC 43 60 569 12 REC 44 60 569 12 Repeat pt per acoustics request REC 45 60 569 25 REC 46 60 569 35 REC 47 60 569 45 REC 48 60 569 55 REC 49 60 569 65 Run TR092RN022 continued Point Data Yaw, Rotor q , Notes Type Point deg RPM psf REC 50 60 569 75 REC 51 60 569 65 REC 52 60 569 55 REC 53 60 569 55 Repeat pt per acoustics request REC 54 60 569 45 REC 55 60 569 35 REC 56 60 569 25 REC 57 60 569 12 REC 58 60 SIM 12 REC 59 75 SIM 12 REC 60 75 569 12 REC 61 75 569 25 REC 62 75 569 35 REC 63 75 569 45 REC 64 75 569 55 REC 65 75 569 65 REC 66 75 569 65 Repeat, q was too high for previous point REC 67 75 569 75 REC 68 75 569 65 REC 69 75 569 55 REC 70 75 569 45 REC 71 75 569 35 REC 72 75 569 25 REC 73 75 569 12 REC 74 75 SIM 12 REC 75 75 SIM 12 Repeat pt per acoustics request REC 76 90 SIM 12 REC 77 90 569 12 REC 78 90 569 16 REC 79 92 569 16 REC 80 94 569 16 REC 81 96 569 16 REC 82 98 569 16 REC 83 100 569 16 REC 84 98 569 16 REC 85 96 569 16 REC 86 94 569 16 REC 87 92 569 16 REC 88 90 569 16 REC 89 88 569 16 REC 90 86 569 16 REC 91 84 569 16 REC 92 82 569 16 REC 93 80 569 16 REC 94 82 569 16 REC 95 84 569 16 REC 96 86 569 16 REC 97 88 569 16 REC 98 90 569 16 REC 99 90 569 12 REC 100 90 SIM 12 REC 101 90 569 12 Run TR092RN022 continued Point Data Yaw, Rotor q , Notes Type Point deg RPM psf REC 102 90 569 22 REC 103 92 569 22 REC 104 94 569 22 REC 105 96 569 22 REC 106 98 569 22 REC 107 100 569 22 REC 108 98 569 22 REC 109 96 569 22 REC 110 94 569 22 REC 111 92 569 22 REC 112 90 569 22 REC 113 88 569 22 REC 114 86 569 22 REC 115 84 569 22 REC 116 82 569 22 REC 117 80 569 22 REC 118 82 569 22 REC 119 84 569 22 REC 120 86 569 22 REC 121 88 569 22 REC 122 90 569 22 REC 123 90 569 12 REC 124 90 SIM 12 REC 125 90 569 12 REC 126 90 569 29 REC 127 92 569 29 REC 128 94 569 29 REC 129 96 569 29 REC 130 98 569 29 REC 131 100 569 29 REC 132 98 569 29 REC 133 96 569 29 REC 134 94 569 29 REC 135 92 569 29 REC 136 90 569 29 REC 137 88 569 29 REC 138 86 569 29 REC 139 84 569 29 REC 140 82 569 29 REC 141 80 569 29 REC 142 82 569 29 REC 143 84 569 29 REC 144 86 569 29 REC 145 88 569 29 REC 146 90 569 29 REC 147 90 569 12 REC 148 90 SIM 12 REC 149 90 569 12 REC 150 90 569 36 REC 151 92 569 36 REC 152 94 569 36 REC 153 96 569 36 Run TR092RN022 continued Point Data Yaw, Rotor q , Notes Type Point deg RPM psf REC 154 98 569 36 REC 155 100 569 36 REC 156 98 569 36 REC 157 96 569 36 REC 158 94 569 36 REC 159 92 569 36 REC 160 90 569 36 REC 161 88 569 36 REC 162 86 569 36 REC 163 84 569 36 REC 164 82 569 36 REC 165 80 569 36 REC 166 82 569 36 REC 167 84 569 36 REC 168 86 569 36 REC 169 88 569 36 REC 170 90 569 36 REC 171 90 569 12 REC 172 90 SIM 12 REC 173 90 SIM 0 REC 174 90 SIM 0 ZER 175 90 SIM 0 CAL 176 90 SIM 0 Table 7. TTR/699 Run Log (continued) Run TR092RN024 5/12/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 SIM 0 CAL 2 0 SIM 0 AB ZER 3 90 SIM 0 CAL 4 90 SIM 0 ZER 5 90 SIM 0 CAL 6 90 SIM 0 REC 7 90 SIM 0 STATIC REC 8 90 SIM 0 REC 9 90 200 0 REC 10 90 400 0 Cont 11-20 90 569 0 Cont 21-29 90-0 569 0 moving yaw to 0 during data collection Cont 30-37 0 569 0 REC 38 90 569 0 REC 39 90 200 0 STATIC ZER 40 0 SIM 0 CAL 41 0 SIM 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN025 5/12/2017 Yaw sweep, 569 rpm, q = 12 psf Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 SIM 0 CAL 2 0 SIM 0 AB ZER 3 0 SIM 0 CAL 4 0 SIM 0 REC 5 0 SIM 0 STATIC REC 6 0 569 0 REC 7 0 569 0 REC 8 15 569 0 REC 9 30 569 0 REC 10 45 569 0 REC 11 60 569 0 REC 12 75 569 0 REC 13 90 SIM 0 STATIC ZER 14 90 SIM 0 CAL 15 90 SIM 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN026 5/12/2017 Acoustic/heating run, 90 deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 90 SIM 0 CAL 2 90 SIM 0 AB ZER 3 90 SIM 0 CAL 4 90 SIM 0 REC 5 90 SIM 0 STATIC REC 6 90 201 0 REC 7 90 401 0 REC 8 90 570 0 REC 9 90 553 16 REC 10 90 552 16 REC 11 90 552 16 REC 12 90 552 16 REC 13 90 553 16 REC 14 90 554 16 REC 15 90 553 22 REC 16 90 553 22 REC 17 90 553 22 REC 18 90 553 22 REC 19 90 553 22 REC 20 90 553 22 REC 21 90 553 28 REC 22 90 553 28 REC 23 90 553 28 REC 24 90 553 28 REC 25 90 554 28 REC 26 90 554 28 REC 27 90 569 0 REC 28 90 401 0 REC 29 90 200 0 REC 30 90 SIM 0 rotations set at 64 ZER 31 90 SIM 0 CAL 32 90 SIM 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN027 5/12/2017 q sweep, 569 rpm, 90 deg yaw Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 90 SIM 0 sdas at 16 ZER 2 90 SIM 0 CAL 3 90 SIM 0 AB ZER 4 90 SIM 0 CAL 5 90 SIM 0 REC 6 90 SIM 0 STATIC REC 7 90 569 0 REC 8 90 569 12 REC 9 90 569 16 REC 10 90 569 29 REC 11 90 569 36 REC 12 90 569 29 REC 13 90 569 16 REC 14 90 569 12 REC 15 90 569 0 REC 16 90 SIM 0 Bad point REC 17 90 SIM 0 STATIC ZER 18 90 SIM 0 CAL 19 90 SIM 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN028 5/12/2017 Yaw sweeps, 569 rpm, q = 12 psf Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 90 SIM 0 CAL 2 90 SIM 0 AB ZER 3 90 SIM 0 CAL 4 90 SIM 0 REC 5 90 SIM 0 STATIC REC 6 90 570 0 REC 7 90 570 12 REC 8 75 569 12 REC 9 60 569 12 REC 10 45 569 12 REC 11 30 569 12 REC 12 15 570 12 REC 13 0 569 12 REC 14 15 569 12 REC 15 30 569 12 REC 16 45 569 12 REC 17 60 569 12 REC 18 75 569 12 REC 19 90 569 12 REC 20 75 570 12 REC 21 60 570 12 REC 22 45 570 12 REC 23 30 570 12 REC 24 15 570 12 REC 25 0 570 12 REC 26 90 570 12 REC 27 90 569 0 REC 28 90 SIM 0 STATIC ZER 29 90 SIM 0 CAL 30 90 SIM 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN030 5/17/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 ZERO CAL 2 0 0 0 RCAL ZER 3 0 0 0 ZERO (AB) CAL 4 0 0 0 RCAL ZER 5 0 0 0 ZERO (AB) REC 6 0 200 0 REC 7 0 400 0 REC 8 0 569 0 Cont 9 - 32 0 569 0 Hold for 60 min or heat stabilizes, periodic data every min REC 33 0 200 0 REC 34 0 0 0 Static Point ZER 35 0 0 0 ZERO CAL 36 0 0 0 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN031 5/17/2017 Yaw sweep, 569 rpm, q =36psf Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 SIM 0 CAL 2 0 SIM 0 AB ZER 3 0 SIM 0 CAL 4 0 SIM 0 ZER 5 0 SIM 0 CAL 6 0 SIM 0 ZER 7 0 SIM 0 CAL 8 0 SIM 12 REC 9 0 SIM 36 REC 10 0 569 36 REC 11 0 569 36 No tunnel condition data entered REC 12 0 569 36 No tunnel condition data entered REC 13 0 569 36 Repeat for tunnel conditions REC 14 15 569 36 REC 15 30 569 36 REC 16 45 569 36 REC 17 60 569 36 REC 18 63 569 36 REC 19 65 569 36 REC 20 67 569 36 REC 21 69 569 36 REC 22 71 569 36 REC 23 73 569 36 REC 24 75 569 36 REC 25 77 569 36 REC 26 80 569 36 REC 27 82 569 36 REC 28 84 569 36 REC 29 86 569 36 REC 30 88 569 36 REC 31 90 569 36 REC 32 92 569 36 REC 33 94 569 36 REC 34 96 569 36 REC 35 98 569 12 REC 36 100 569 12 REC 37 90 569 0 REC 38 90 569 0 REC 39 0 569 0 REC 40 0 569 0 REC 41 0 SIM 0 ZER 42 0 SIM 0 CAL 43 0 SIM 0 Table 7. TTR/699 Run Log (continued) Run TR092RN032 5/17/2017 Heating run Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 0 0 CAL 2 0 0 0 AB ZER 3 0 0 0 CAL 4 0 0 0 REC 5 0 0 0 REC 6 0 200 0 REC 7 0 400 0 REC 8 0 569 0 Cont 9 - 24 0 569 0 Hold for 60 min or heat stabilizes, periodic data every min REC 25 0 200 0 REC 26 0 0 0 ZER 27 0 0 0 CAL 28 0 0 0 AB Table 7. TTR/699 Run Log (continued) Run TR092RN033 5/17/2017 Yaw sweeps, 569 and 0 rpm, q =75psf Aerotares: Blades Off, Spinner Fairing and Fairing Close-Outs Installed Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 SIM 0 CAL 2 0 SIM 0 ZER 3 0 SIM 0 CAL 4 0 SIM 0 REC 5 0 SIM 0 REC 6 0 570 12 Incorrect inputs REC 7 0 569 12 Repeat pt REC 8 0 569 75 REC 9 15 569 75 REC 10 30 569 75 REC 11 45 569 75 REC 12 60 569 75 REC 13 63 569 75 REC 14 65 569 75 REC 15 67 569 75 REC 16 69 569 75 REC 17 71 570 75 REC 18 73 570 75 REC 19 75 570 75 REC 20 77 570 75 REC 21 80 570 75 REC 22 82 570 75 REC 23 84 569 75 REC 24 86 569 75 REC 25 88 569 75 REC 26 90 570 75 REC 27 92 569 75 REC 28 94 570 75 REC 29 96 570 75 REC 30 98 570 75 REC 31 100 570 75 REC 32 90 570 75 REC 33 90 570 75 REC 34 90 479 75 REC 35 90 401 75 REC 36 90 300 75 REC 37 90 200 75 REC 38 90 100 75 REC 39 90 SIM 75 REC 40 90 SIM 12 REC 41 0 SIM 12 REC 42 0 SIM 75 REC 43 15 SIM 75 AB REC 44 30 SIM 75 REC 45 30 SIM 75 REC 46 45 SIM 75 REC 47 60 SIM 75 REC 48 65 SIM 75 REC 49 70 SIM 75 Run TR092RN033 continued Point Data Yaw, Rotor q , Notes Type Point deg RPM psf REC 50 75 SIM 75 REC 51 80 SIM 75 REC 52 85 SIM 75 REC 53 90 SIM 75 REC 54 95 SIM 75 REC 55 100 SIM 75 REC 56 90 SIM 75 REC 57 90 SIM 12 REC 58 0 SIM 0 ZER 59 0 SIM 0 CAL 60 0 SIM 0 Table 7. TTR/699 Run Log (continued) Run TR092RN036 5/23/2017 Buildup: blade installation, wind off -45 deg yaw for blade installation Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 - 45 SIM 0 CAL 2 - 45 SIM 0 AB ZER 3 - 45 SIM 0 CAL 4 - 45 SIM 0 Zero'd AMPs PNL 60 ZER 5 - 45 SIM 0 CAL 6 - 45 SIM 0 ZER 7 - 45 SIM 0 CAL 8 - 45 SIM 0 REC 9 - 45 SIM 0 two blades installed REC 10 - 45 SIM 0 repeat point REC 11 - 45 SIM 0 before Red blade install REC 12 - 45 SIM 0 REC 13 - 45 SIM 0 Static ZER 14 - 45 SIM 0 CAL 15 - 45 SIM 0 Table 7. TTR/699 Run Log (continued) Run TR092RN047 6/9/2017 Hover balancing run, wind off - nominal blade tip weights Air Exchange Open 100%, Vane Set 3,4, & 6 in 80x Mode; Balance heater off Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 25 Not at 25 collective CAL 2 0 SIM 25 Not at 25 collective ZER 3 0 SIM 25 Not at 25 collective CAL 4 0 SIM 25 Not at 25 collective ZER 5 0 SIM 25 CAL 6 0 SIM 25 AB ZER 7 0 SIM 25 CAL 8 0 SIM 25 REC 9 0 SIM 5 static REC 10 0 82 5 REC 11 0 164 5 REC 12 0 247 5 REC 13 0 329 5 REC 14 0 410 5 REC 15 0 479 5 REC 16 0 569 5 REC 17 0 570 4 REC 18 0 570 3 REC 19 0 478 5 REC 20 0 478 5 cyclic delta from 0 - flapping trim REC 21 0 478 5 cyclic delta REC 22 0 478 5 cyclic delta REC 23 0 478 5 cyclic delta REC 24 0 478 5 cyclic delta REC 25 0 478 5 cyclic delta REC 26 0 478 5 cyclic delta REC 27 0 478 5 REC 28 0 SIM 5 static ZER 29 0 SIM 25 CAL 30 0 SIM 25 Table 7. TTR/699 Run Log (continued) Run TR092RN049 8/21/2017 Hover balancing run, wind off - new blade tip weights Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 25 CAL 2 0 SIM 25 AB ZER 3 0 SIM 25 CAL 4 0 SIM 25 ZER 5 0 SIM 25 CAL 6 0 SIM 25 AB ZER 7 0 SIM 25 CAL 8 0 SIM 25 REC 9 0 SIM 5 static REC 10 0 83 5 REC 11 0 165 5 REC 12 0 247 5 REC 13 0 328 5 REC 14 0 410 5 REC 15 0 478 5 REC 16 0 569 5 REC 17 0 569 5 REC 18 0 569 5 REC 19 0 570 5 REC 20 0 570 5 REC 21 0 570 5 REC 22 0 570 5 REC 23 0 569 5 REC 24 0 569 5 REC 25 0 569 5 REC 26 0 479 5 REC 27 0 479 6 REC 28 0 478 7 REC 29 0 478 8 REC 30 0 478 9 REC 31 0 478 10 REC 32 0 478 11 REC 33 0 569 10 REC 34 0 569 10 REC 35 0 200 5 REC 36 0 SIM 5 static ZER 37 0 SIM 25 CAL 38 0 SIM 25 Table 7. TTR/699 Run Log (continued) Run TR092RN050 8/22/2017 Hover balancing run, wind off - new blade tip weights Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 25 CAL 2 0 SIM 25 AB ZER 3 0 SIM 25 CAL 4 0 SIM 25 REC 5 0 SIM 5 static REC 6 0 82 5 REC 7 0 164 5 REC 8 0 200 5 REC 9 0 246 5 REC 10 0 328 5 REC 11 0 410 5 REC 12 0 478 5 REC 13 0 570 5 REC 14 0 570 5 REC 15 0 570 5 REC 16 0 201 5 REC 17 0 SIM 5 static ZER 18 0 SIM 25 CAL 19 0 SIM 25 Table 7. TTR/699 Run Log (continued) Run TR092RN051 8/22/2017 Hover balancing run – run 50 tip weights, removed rotating scissor weight Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 25 CAL 2 0 SIM 25 AB ZER 3 0 SIM 25 CAL 4 0 SIM 25 REC 5 0 SIM 5 static REC 6 0 82 5 REC 7 0 165 5 REC 8 0 201 5 REC 9 0 247 5 REC 10 0 328 5 REC 11 0 411 5 REC 12 0 478 5 REC 13 0 201 5 REC 14 0 SIM 5 static ZER 15 0 SIM 25 CAL 16 0 SIM 25 Table 7. TTR/699 Run Log (continued) Run TR092RN055 3/19/2018 Hover balancing run – Green weight 233.6 g, White weight 177.7 g Air Exchange Open 50%, Louver 7 Closed, 40x Mode Rotating counterweight removed, swashplate balancing plate installed (no weights installed) Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 SIM 5 static REC 6 0 82 5 REC 7 0 164 5 REC 8 0 200 5 REC 9 0 246 5 REC 10 0 328 5 REC 11 0 411 5 REC 12 0 479 5 REC 13 0 570 5 REC 14 0 201 5 REC 15 0 SIM 5 static ZER 16 0 SIM 15 CAL 17 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN056 3/19/2018 Hover balancing run – Green weight 233.6 g, White weight 177.7 g Air Exchange Open 100%, Louver 7 Closed, 40x Mode Rotating counterweight removed, swashplate balancing plate installed (all weights installed, 1722 g added) Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 ZER 5 0 SIM 15 CAL 6 0 SIM 15 REC 7 0 SIM 15 static REC 8 0 SIM 5 static REC 9 0 82 5 REC 10 0 164 5 REC 11 0 200 5 REC 12 0 246 5 REC 13 0 328 5 REC 14 0 410 5 REC 15 0 478 5 REC 16 0 569 5 REC 17 0 479 5 REC 18 0 411 5 REC 19 0 328 5 REC 20 0 247 5 REC 21 0 201 5 REC 22 0 165 5 REC 23 0 83 5 REC 24 0 SIM 5 static REC 25 0 SIM 15 static ZER 26 0 SIM 15 CAL 27 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN057 3/19/2018 Hover balancing run – Green weight 177.8 g, White weight 177.7 g Air Exchange Open 100%, Louver 7 Closed, 40x Mode Rotating counterweight removed, swashplate balancing plate installed (all weights installed, 1722 g) Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 SIM 15 static REC 6 0 SIM 5 static REC 7 0 82 5 REC 8 0 164 5 REC 9 0 200 5 REC 10 0 246 5 REC 11 0 328 5 REC 12 0 410 5 REC 13 0 478 5 REC 14 0 570 5 REC 15 0 479 5 REC 16 0 411 5 REC 17 0 329 5 REC 18 0 246 5 REC 19 0 201 5 REC 20 0 165 5 REC 21 0 83 5 REC 22 0 SIM 5 static REC 23 0 SIM 15 static ZER 24 0 SIM 15 CAL 25 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN058 3/20/2018 Hover balancing run – Green weight 123.2 g, White weight 177.7 g Air Exchange Open 100%, Louver 7 Closed, 40x Mode Rotating counterweight removed, swashplate balancing plate installed (all weights installed, 1722 g added) Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 ZER 5 0 SIM 15 CAL 6 0 SIM 15 REC 7 0 SIM 15 static REC 8 0 SIM 5 static REC 9 0 82 5 REC 10 0 164 5 REC 11 0 201 5 REC 12 0 246 5 REC 13 0 328 5 REC 14 0 411 5 REC 15 0 479 5 REC 16 0 569 5 REC 17 0 479 5 REC 18 0 411 5 REC 19 0 328 5 REC 20 0 247 5 REC 21 0 201 5 REC 22 0 165 5 REC 23 0 83 5 REC 24 0 SIM 5 static REC 25 0 SIM 15 static ZER 26 0 SIM 15 CAL 27 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN059 3/26/2018 Thrust checkout, 0 deg yaw, rpm sweep, wind off Air Exchange Open 100%, Vane Set 3 open, VS 4, 6 & 7 closed 1 Rotating counterweight removed, swashplate balancing plate installed (all weights installed, 1722 g added) Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 ZER 5 0 SIM 15 CAL 6 0 SIM 15 REC 7 0 2 499 15 9 static REC 8 0 2 499 5 5 static REC 9 0 2 82 5 32 REC 10 0 3 164 5 249 REC 11 0 4 200 5 375 REC 12 0 5 246 5 598 REC 13 0 7 328 5 1113 REC 14 0 10 410 5 1744 REC 15 0 12 478 5 2396 REC 16 0 16 569 5 3411 REC 17 0 17 569 5 3308 cyclic delta from 0 - flapping trim REC 18 0 17 569 5 3349 cyclic delta REC 19 0 17 569 5 3298 cyclic delta REC 20 0 17 569 5 3338 cyclic delta REC 21 0 17 569 5 3327 cyclic delta REC 22 0 17 569 5 3364 REC 23 0 16 569 4 2853 REC 24 0 17 569 5 3375 REC 25 0 18 569 6 3923 REC 26 0 17 569 5 3303 REC 27 0 16 569 4 2844 REC 28 0 15 569 3 2419 REC 29 0 15 569 2 2171 hit SOF limit REC 30 0 17 569 5 3349 REC 31 0 16 478 5 2235 REC 32 0 13 410 5 1606 REC 33 0 11 328 5 995 REC 34 0 9 246 5 524 REC 35 0 7 200 5 346 REC 36 0 6 164 5 225 REC 37 0 5 82 5 43 REC 38 0 4 499 5 - 4 static REC 39 0 3 499 15 - 8 static ZER 40 0 SIM 15 CAL 41 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN060 3/26/2018 Thrust checkout, 0 deg yaw, 569 rpm, wind off Air Exchange Open 100%, Vane Set 3 Open, VS 4, 6 & 7 Closed Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 3 499 15 - 1 static REC 6 0 3 499 5 - 11 static REC 7 0 4 199 5 410 REC 8 0 15 569 5 3486 REC 9 0 19 569 7 4392 REC 10 0 22 568 9 5569 REC 11 0 25 569 11 6691 REC 12 0 27 568 13 7902 REC 13 0 29 568 14 8446 REC 14 0 30 569 15 8999 hit SOF limits REC 15 0 30 569 15 8971 REC 16 0 29 569 14 8521 REC 17 0 28 569 13 7883 REC 18 0 26 569 11 6612 REC 19 0 23 569 9 5472 REC 20 0 20 569 7 4379 REC 21 0 18 569 5 3355 REC 22 0 10 200 5 287 REC 23 0 5 499 5 1 static REC 24 0 4 499 15 3 static ZER 25 0 499 15 CAL 26 0 499 15 Table 7. TTR/699 Run Log (continued) Run TR092RN061 3/27/2018 Thrust checkout, 0 deg yaw, 569 rpm, wind off Air Exchange Open 100%, Vane Set 3 Open, VS 4, 6 & 7 Closed Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 0 499 15 6 static REC 6 0 0 499 5 9 static REC 7 0 0 200 5 393 REC 8 0 17 569 5 3273 REC 9 0 19 569 7 4262 REC 10 0 21 569 9 5423 REC 11 0 24 569 11 6498 REC 12 0 27 569 13 7700 REC 13 0 28 569 14 8260 REC 14 0 30 569 15 8851 REC 15 0 31 569 16 9436 REC 16 0 32 569 17 10069 REC 17 0 31 570 16 9432 REC 18 0 30 570 15 8864 REC 19 0 29 569 14 8226 REC 20 0 27 569 13 7637 REC 21 0 25 569 11 6433 REC 22 0 22 569 9 5348 REC 23 0 20 569 7 4257 REC 24 0 17 569 5 3256 REC 25 0 9 200 5 282 REC 26 0 4 499 5 8 static REC 27 0 3 499 15 - 4 static ZER 28 0 SIM 15 CAL 29 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN062 3/27/2018 Thrust checkout, 180 deg yaw, 569 rpm, wind off Air Exchange Open 100%, Vane Set 3 Open, VS 4, 6 & 7 Closed Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM deg lb ZER 1 180 SIM 15 CAL 2 180 SIM 15 AB ZER 3 180 SIM 15 CAL 4 180 SIM 15 REC 5 180 3 499 15 - 7 static REC 6 180 3 499 5 - 9 static REC 7 180 5 200 5 393 REC 8 180 10 569 5 3893 REC 9 180 10 569 7 5158 REC 10 180 12 569 9 6330 REC 11 180 12 569 11 7629 REC 12 180 14 569 13 9039 REC 13 180 14 570 14 9708 REC 14 180 16 569 15 10339 REC 15 180 16 568 16 10965 REC 16 180 16 568 17 11471 REC 17 180 16 568 16 10981 REC 18 180 14 569 15 10362 REC 19 180 16 569 14 9804 REC 20 180 15 569 13 9046 REC 21 180 12 569 11 7677 REC 22 180 12 569 9 6353 REC 23 180 11 569 7 5164 REC 24 180 7 569 5 3990 REC 25 180 4 200 5 438 REC 26 180 3 499 5 10 static REC 27 180 3 499 15 1 static ZER 28 180 SIM 15 CAL 29 180 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN063 3/27/2018 Thrust checkout, 180 deg yaw, 569 rpm, wind off Air Exchange Open 100%, Vane Set 3 Closed, VS 4, 6 & 7 Open Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM deg lb ZER 1 180 SIM 15 CAL 2 180 SIM 15 AB ZER 3 180 SIM 15 CAL 4 180 SIM 15 REC 5 180 3 499 15 6 static REC 6 180 3 499 5 5 static REC 7 180 6 200 5 416 REC 8 180 9 569 5 3937 REC 9 180 9 569 7 5080 REC 10 180 12 570 9 6474 REC 11 180 11 570 11 7706 REC 12 180 14 570 13 9099 REC 13 180 13 570 14 9745 REC 14 180 14 569 15 10415 REC 15 180 15 569 16 11017 REC 16 180 15 570 17 11419 REC 17 180 14 570 16 11129 REC 18 180 17 569 15 10463 REC 19 180 15 570 14 9756 REC 20 180 13 569 13 9054 REC 21 180 10 569 11 7689 REC 22 180 11 570 9 6497 REC 23 180 9 569 7 5192 REC 24 180 11 569 5 3994 REC 25 180 4 200 5 441 REC 26 180 4 499 5 14 static REC 27 180 4 499 15 4 static ZER 28 180 SIM 15 CAL 29 180 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN071 7/26/2018 Swashplate Balance tare, RPM sweep, 15 deg collective, wind off Blades Off, Spinner Fairing and Nose Cone Installed Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 0 15 CAL 2 0 0 15 ZER 3 0 0 15 CAL 4 0 0 15 REC 5 0 0 15 STATIC REC 6 0 60 15 REC 7 0 100 15 REC 8 0 150 15 REC 9 0 200 15 REC 10 0 250 15 REC 11 0 300 15 REC 12 0 350 15 REC 13 0 400 15 REC 14 0 450 15 REC 15 0 479 15 REC 16 0 525 15 REC 17 0 570 15 REC 18 0 526 15 REC 19 0 478 15 REC 20 0 450 15 REC 21 0 400 15 REC 22 0 350 15 REC 23 0 300 15 REC 24 0 251 15 REC 25 0 201 15 REC 26 0 151 15 REC 27 0 100 15 REC 28 0 60 15 REC 29 0 0 15 STATIC ZER 30 0 0 15 CAL 31 0 0 15 Table 7. TTR/699 Run Log (continued) Run TR092RN072 7/26/2018 Swashplate balance tare, collective sweep, 569 rpm, wind off Blades Off, Spinner Fairing and Nose Cone Installed Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg ZER 1 0 0 15 CAL 2 0 0 15 ZER 3 0 0 15 CAL 4 0 0 15 REC 5 0 499 15 STATIC REC 6 0 569 15 REC 7 0 568 - 5 REC 8 0 569 0 REC 9 0 569 5 REC 10 0 569 10 REC 11 0 569 15 REC 12 0 569 20 REC 13 0 569 25 REC 14 0 569 30 REC 15 0 569 35 REC 16 0 569 40 REC 17 0 569 45 REC 18 0 569 50 REC 19 0 569 45 REC 20 0 569 40 REC 21 0 569 35 REC 22 0 569 30 REC 23 0 569 25 REC 24 0 569 20 REC 25 0 569 15 REC 26 0 569 10 REC 27 0 569 5 REC 28 0 569 0 REC 29 0 569 - 5 REC 30 0 479 - 5 REC 31 0 478 0 REC 32 0 479 5 REC 33 0 479 10 REC 34 0 478 15 REC 35 0 478 20 REC 36 0 478 25 REC 37 0 478 30 REC 38 0 479 35 REC 39 0 479 40 REC 40 0 479 45 REC 41 0 479 50 REC 42 0 479 45 REC 43 0 479 40 REC 44 0 479 35 REC 45 0 479 30 REC 46 0 479 25 REC 47 0 479 20 REC 48 0 479 15 REC 49 0 479 10 Run TR092RN072 continued Point Data Yaw, Rotor Coll., Notes Type Point deg RPM deg REC 50 0 479 5 REC 51 0 479 0 REC 52 0 479 - 5 REC 53 0 387 - 5 REC 54 0 387 0 REC 55 0 387 5 REC 56 0 387 10 REC 57 0 388 15 REC 58 0 388 20 REC 59 0 388 25 REC 60 0 388 30 REC 61 0 388 35 REC 62 0 387 40 REC 63 0 387 45 REC 64 0 388 50 REC 65 0 388 45 REC 66 0 387 40 REC 67 0 387 35 REC 68 0 388 30 REC 69 0 387 25 REC 70 0 388 20 REC 71 0 387 15 REC 72 0 388 10 REC 73 0 387 5 REC 74 0 388 0 REC 75 0 388 - 5 REC 76 0 569 15 REC 77 0 499 15 STATIC ZER 78 0 0 15 ZERO CAL 79 0 0 15 RCAL Table 7. TTR/699 Run Log (continued) Run TR092RN074 8/8/2018 Post - IST hover checkout, rpm and collective sweeps, 0 deg yaw, wind off Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM/ deg lb M tip ZER 1 0 0 SIM 15 CAL 2 0 0 SIM 15 ZER 3 0 0 SIM 15 CAL 4 0 0 SIM 15 REC 5 0 0 499 15 6 REC 6 0 0 499 5 12 REC 7 0 0 83 5 33 REC 8 0 0 164 5 258 REC 9 0 3 200 5 408 REC 10 0 4 246 5 638 REC 11 0 6 328 5 1176 REC 12 0 9 410 5 1900 REC 13 0 11 478 5 2604 REC 14 0 14 569 5 3760 REC 15 0 14 478 5 2501 REC 16 0 12 411 5 1795 REC 17 0 9 328 5 1095 REC 18 0 7 247 5 601 REC 19 0 5 201 5 392 REC 20 0 3 165 5 269 REC 21 0 0 82 5 67 REC 22 0 13 569 5 3853 REC 23 0 16 569 5 3640 switched to TTF_ANA REC 24 0 15 569 5 3666 cyclic delta from 0 - flapping trim REC 25 0 16 570 5 3655 cyclic delta REC 26 0 15 569 5 3671 cyclic delta REC 27 0 15 569 5 3706 cyclic delta REC 28 0 15 569 5 3660 cyclic delta REC 29 0 15 569 5 3673 REC 30 0 15 0.684 5 3625 change rotor speed ref. to M tip REC 31 0 16 0.685 6 4119 REC 32 0 17 0.684 7 4668 REC 33 0 20 0.684 9 5783 REC 34 0 22 0.684 11 6956 REC 35 0 25 0.684 13 8133 REC 36 0 26 0.684 14 8718 REC 37 0 27 0.685 15 9354 REC 38 0 28 0.684 16 9956 REC 39 0 28 0.684 17 10,352 expect to hit load limit REC 40 0 28 0.684 16.5 9980 REC 41 0 27 0.684 15 9372 REC 42 0 26 0.685 14 8730 REC 43 0 25 0.684 13 8133 REC 44 0 23 0.684 11 6913 REC 45 0 21 0.685 9 5731 REC 46 0 18 0.685 7 4658 REC 47 0 15 0.684 5 3592 REC 48 0 1 83 5 48 Run TR092RN074 continued Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM/ deg lb M tip REC 49 0 0 499 5 12 static REC 50 0 0 499 15 - 3 static ZER 51 0 0 499 15 - 4 CAL 52 0 0 499 15 Table 7. TTR/699 Run Log (continued) Run TR092RN075 8/13/2018 Airplane forward flight, thrust sweep, 478 rpm, 60 & 90 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 0 SIM ZER 2 0 SIM CAL 3 0 SIM ZER 4 0 SIM CAL 5 0 SIM REC 6 0 499 REC 7 0 499 REC 8 0 200 Rotating ref. point REC 9 0 7 479 2769 0.018 0.058 Airplane mode rpm ref. point REC 10 0 61 0.583 508 0.156 0.011 nominal fwd flight ref. point (1) REC 11 0 61 0.583 552 0.156 0.012 cyclic delta from 0 - flapping trim REC 12 0 61 0.583 489 0.156 0.010 cyclic delta REC 13 0 61 0.583 456 0.156 0.010 cyclic delta REC 14 0 61 0.583 488 0.156 0.010 cyclic delta REC 15 0 61 0.583 552 0.156 0.012 cyclic delta REC 16 0 61 0.583 491 0.156 0.010 cyclic delta REC 17 0 61 0.583 467 0.156 0.010 cyclic delta REC 18 0 61 0.583 500 0.156 0.010 REC 19 0 61 0.583 1003 0.156 0.021 REC 20 0 61 0.583 1450 0.157 0.030 REC 21 0 61 0.583 1935 0.156 0.040 REC 22 0 61 0.583 2444 0.156 0.051 REC 23 0 61 0.583 2917 0.157 0.061 REC 24 0 61 0.583 3371 0.156 0.070 REC 25 0 61 0.583 3858 0.157 0.081 REC 26 0 61 0.583 4313 0.157 0.090 REC 27 0 61 0.583 4809 0.156 0.100 REC 28 0 61 0.583 5317 0.156 0.111 REC 29 0 61 0.583 5767 0.157 0.120 REC 30 0 61 0.583 6249 0.156 0.130 REC 31 0 61 0.583 6746 0.156 0.141 REC 32 0 61 0.583 478 0.157 0.010 Return to low thrust; nominal ref. pt REC 33 0 91 0.583 514 0.233 0.011 REC 34 0 91 0.583 672 0.233 0.014 cyclic delta REC 35 0 91 0.583 600 0.233 0.013 cyclic delta REC 36 0 91 0.584 546 0.233 0.011 cyclic delta REC 37 0 91 0.583 661 0.233 0.014 cyclic delta REC 38 0 91 0.583 754 0.233 0.016 cyclic delta REC 39 0 91 0.583 727 0.233 0.015 cyclic delta REC 40 0 91 0.583 699 0.234 0.015 cyclic delta REC 41 0 91 0.583 493 0.233 0.010 cyclic delta REC 42 0 92 0.583 1010 0.234 0.021 REC 43 0 91 0.583 1449 0.233 0.030 REC 44 0 91 0.584 1930 0.233 0.040 REC 45 0 92 0.583 2376 0.234 0.050 REC 46 0 91 0.583 2859 0.233 0.060 REC 47 0 91 0.583 3384 0.233 0.071 (1) Set rpm, then match M tip Run TR092RN075 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 48 0 92 0.583 3851 0.234 0.081 REC 49 0 92 0.584 4298 0.234 0.090 REC 50 0 91 0.583 4812 0.233 0.101 REC 51 0 91 0.583 560 0.233 0.012 REC 52 0 61 0.583 489 0.157 0.010 nominal fwd - flight ref. point REC 53 0 12 479 2479 0.031 0.053 hover ref. point REC 54 0 200 REC 55 0 499 static REC 56 0 499 static ZER 57 0 SIM CAL 58 0 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN076 8/13/2018 Airplane forward flight, thrust sweep, 478 rpm, 120 & 150 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb (1) M tip ZER 1 0 SIM CAL 2 0 SIM ZER 3 0 SIM CAL 4 0 SIM REC 5 0 SIM REC 6 0 SIM REC 7 0 0 200 418 0.000 0.0510 Rotating ref. point REC 8 0 9 478 2611 0.022 0.0559 Airplane mode rpm ref. point REC 9 0 61 0.584 472 0.156 0.0098 nominal fwd flight ref. point REC 10 0 122 0.583 543 0.311 0.0115 REC 11 0 122 0.583 537 0.311 0.0114 cyclic delta from 0 - flapping trim REC 12 0 122 0.583 538 0.311 0.0114 cyclic delta REC 13 0 122 0.584 504 0.311 0.0107 cyclic delta REC 14 0 122 0.583 512 0.311 0.0108 cyclic delta REC 15 0 122 0.583 536 0.311 0.0114 cyclic delta REC 16 0 122 0.584 494 0.311 0.0105 cyclic delta REC 17 0 122 0.584 508 0.311 0.0107 cyclic delta REC 18 0 122 0.583 513 0.311 0.0109 REC 19 0 122 0.583 949 0.312 0.0201 REC 20 0 122 0.583 1455 0.312 0.0308 REC 21 0 122 0.583 1939 0.312 0.0411 REC 22 0 122 0.583 2338 0.312 0.0497 REC 23 0 122 0.583 2891 0.311 0.0614 REC 24 0 123 0.583 3284 0.313 0.0697 REC 25 0 123 0.583 3846 0.313 0.0816 REC 26 0 122 0.583 428 0.311 0.0091 REC 27 0 152 0.583 472 0.389 0.0101 REC 28 0 152 0.583 451 0.389 0.0097 cyclic delta REC 29 0 152 0.584 545 0.389 0.0117 cyclic delta REC 30 0 152 0.584 372 0.388 0.0080 cyclic delta REC 31 0 152 0.584 467 0.388 0.0100 cyclic delta REC 32 0 152 0.583 537 0.388 0.0115 cyclic delta REC 33 0 152 0.584 382 0.388 0.0082 cyclic delta REC 34 0 152 0.584 343 0.388 0.0074 cyclic delta REC 35 0 62 0.583 415 0.157 0.0086 nominal fwd - flight ref. point REC 36 0 13 478 2561 0.033 0.0531 hover ref. point REC 37 0 2 200 384 0.012 0.0471 REC 38 0 SIM static REC 39 0 SIM static ZER 40 0 SIM CAL 41 0 SIM (1) No cooling water Table 7. TTR/699 Run Log (continued) Run TR092RN077 8/14/2018 Airplane forward flight, thrust sweep, 478 rpm, 150, 180, 210 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 0 SIM CAL 2 0 SIM ZER 3 0 SIM CAL 4 0 SIM REC 5 0 SIM REC 6 0 SIM REC 7 0 3 200 431 0.020 0.0515 Rotating ref. point REC 8 0 12 478 2624 0.031 0.0545 Airplane mode rpm ref. point REC 9 0 61 0.583 489 0.156 0.0102 Set cyclic for zero flapping; nominal fwd flight ref. point REC 10 0 151 0.582 502 0.390 0.0108 REC 11 0 151 0.582 745 0.390 0.0161 cyclic delta from 0 - flapping trim REC 12 0 151 0.583 1027 0.390 0.0221 cyclic delta REC 13 0 152 0.582 1186 0.391 0.0256 cyclic delta REC 14 0 151 0.582 1507 0.390 0.0324 cyclic delta REC 15 0 152 0.582 1685 0.391 0.0363 cyclic delta REC 16 0 151 0.582 1991 0.390 0.0429 cyclic delta REC 17 0 152 0.583 2162 0.390 0.0464 cyclic delta REC 18 0 152 0.583 2457 0.391 0.0528 REC 19 0 152 0.582 2602 0.391 0.0560 REC 20 0 152 0.583 2917 0.391 0.0628 REC 21 0 153 0.582 3172 0.392 0.0683 REC 22 0 152 0.583 517 0.389 0.0111 REC 23 0 182 0.583 502 0.468 0.0109 Record initial cyclic before input REC 24 0 182 0.582 499 0.467 0.0109 cyclic delta REC 25 0 182 0.582 607 0.468 0.0133 cyclic delta REC 26 0 182 0.583 509 0.467 0.0111 cyclic delta REC 27 0 182 0.582 516 0.467 0.0113 cyclic delta REC 28 0 182 0.582 589 0.466 0.0129 cyclic delta REC 29 0 182 0.582 622 0.468 0.0136 cyclic delta REC 30 0 182 0.582 543 0.468 0.0119 cyclic delta REC 31 0 182 0.582 576 0.467 0.0126 REC 32 0 182 0.583 798 0.467 0.0174 REC 33 0 182 0.584 982 0.467 0.0214 REC 34 0 182 0.583 1227 0.467 0.0268 REC 35 0 183 0.583 1532 0.469 0.0334 REC 36 0 183 0.584 1750 0.468 0.0380 REC 37 0 183 0.583 1928 0.468 0.0420 REC 38 0 183 0.583 2165 0.469 0.0472 REC 39 0 183 0.583 2357 0.470 0.0515 REC 40 0 183 0.582 2592 0.469 0.0567 REC 41 0 183 0.583 606 0.468 0.0132 REC 42 0 212 0.583 609 0.544 0.0135 Record initial cyclic before input REC 43 0 213 0.583 536 0.545 0.0119 cyclic delta REC 44 0 212 0.583 454 0.544 0.0101 cyclic delta REC 45 0 212 0.583 637 0.544 0.0141 cyclic delta; t unnel auto stopped after point REC 46 0 SIM static REC 47 0 SIM static Run TR092RN077 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 48 0 SIM static ZER 49 0 SIM CAL 50 0 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN078 8/16/2018 Motor current checkout, thrust sweep, 0 deg yaw, 478 rpm, wind off Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Coll., Thrust, Notes Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 SIM 15 REC 6 0 SIM 5 REC 7 0 5 200 5 466 REC 8 0 13 478 5 2601 REC 9 0 14 478 6 2944 REC 10 0 15 479 7 3326 REC 11 0 17 479 9 4119 REC 12 0 19 479 11 4967 REC 13 0 20 479 13 5824 REC 14 0 21 479 14 6250 REC 15 0 22 479 15 6654 REC 16 0 23 478 16 7063 REC 17 0 24 479 17 7488 expect to hit load limit REC 18 0 24 479 18 7899 expect to hit load limit REC 19 0 25 479 19 8268 expect to hit load limit REC 20 0 26 478 20 8601 expect to hit load limit REC 21 0 26 478 21 8827 expect to hit load limit REC 22 0 14 478 5 2534 REC 23 0 7 200 5 394 REC 24 0 SIM 5 static REC 25 0 SIM 15 static ZER 26 0 SIM 15 CAL 27 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN079 8/16/2018 Static rotor control rate check, wind off Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, Rotor Coll., Long. Lateral Notes Type Point deg RPM deg Cyclic, Cyclic, deg deg ZER 1 0 SIM 15 0 0 CAL 2 0 SIM 15 0 0 ZER 3 0 SIM 15 0 0 CAL 4 0 SIM 15 0 0 REC 5 0 SIM 15 0 0 REC 6 0 SIM 15+ 0 0 Rate 4/Emergency: 0.5 deg/sec REC 7 0 SIM 15 - 0 0 REC 8 0 SIM 15 + 0 REC 9 0 SIM 15 - 0 REC 10 0 SIM 15 0 + REC 11 0 SIM 15 0 - REC 12 0 SIM 15+ 0 0 Rate 3: 0.25 deg/sec REC 13 0 SIM 15 - 0 0 REC 14 0 SIM 15 + 0 REC 15 0 SIM 15 - 0 REC 16 0 SIM 15 0 + REC 17 0 SIM 15 0 - REC 18 0 SIM 15+ 0 0 Rate 2: 0.10 deg/sec REC 19 0 SIM 15 - 0 0 REC 20 0 SIM 15 + 0 REC 21 0 SIM 15 - 0 REC 22 0 SIM 15 0 + REC 23 0 SIM 15 0 - REC 24 0 SIM 15+ 0 0 Rate 1: 0.06 deg/sec REC 25 0 SIM 15 - 0 0 REC 26 0 SIM 15 + 0 REC 27 0 SIM 15 - 0 REC 28 0 SIM 15 0 + REC 29 0 SIM 15 0 - REC 30 0 SIM 35+ 0 0 Rate 3: 0.25 deg/sec - High Collective REC 31 0 SIM 35 - 0 0 REC 32 0 SIM 15 0 0 ZER 33 0 SIM 15 0 0 CAL 34 0 SIM 15 0 0 Table 7. TTR/699 Run Log (continued) Run TR092RN080 8/16/2018 Airplane forward flight, operator training, 0 deg yaw, 60, 150, 210 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Rotor VKTS Coll., Thrust, Notes 𝜇 C / 𝜎 T Type Point RPM/ deg lb M tip ZER 1 SIM 15 CAL 2 SIM 15 ZER 3 SIM 15 CAL 4 SIM 15 REC 5 SIM 15 REC 6 SIM 15 REC 7 SIM 5 REC 8 200 0 5 413 0.000 0.0501 Rotating ref. point REC 9 0.583 10 5 2623 0.026 0.0542 Airplane mode rpm ref. point REC 10 0.583 61 11 975 0.157 0.0203 Operating Training – Loaded Rate Check 1094 0.157 0.0229 Control deltas , Blue console: REC 11 0.582 61 + 867 0.157 0.0180 collective delta REC 12 0.583 61 - 993 0.157 0.0207 collective delta REC 13 0.582 61 982 0.157 0.0204 cyclic delta from 0 - flapping trim (1) REC 14 0.583 61 1025 0.157 0.0214 cyclic delta REC 15 0.583 61 992 0.157 0.0206 cyclic delta REC 16 0.583 62 1052 0.156 0.0220 cyclic delta 821 0.156 0.0171 Control deltas , White console: REC 17 0.582 61 + 1012 0.157 0.0211 collective delta REC 18 0.583 61 - 986 0.157 0.0205 collective delta REC 19 0.583 61 1015 0.156 0.0212 cyclic delta from 0 - flapping trim (1) REC 20 0.583 61 1002 0.157 0.0209 cyclic delta REC 21 0.583 61 1013 0.390 0.0217 cyclic delta REC 22 0.583 61 1108 0.392 0.0240 cyclic delta REC 23 0.583 153 28 892 0.389 0.0191 Operating Training – Loaded Rate Check 992 0.391 0.0214 Control deltas , Blue console: REC 24 0.580 153 + 999 0.390 0.0215 collective delta REC 25 0.584 153 - 1041 0.391 0.0224 collective delta REC 26 0.582 153 928 0.390 0.0199 cyclic delta from 0 - flapping trim (1) REC 27 0.582 153 578 0.544 0.0128 cyclic delta REC 28 0.582 153 550 0.542 0.0121 cyclic delta REC 29 0.582 153 558 0.544 0.0123 cyclic delta REC 30 0.583 213 36 685 0.544 0.0152 Record initial cyclic settings before input REC 31 0.584 213 36 584 0.544 0.0129 cyclic delta REC 32 0.583 214 36 546 0.543 0.0121 cyclic delta REC 33 0.582 213 36 506 0.544 0.0112 cyclic delta REC 34 0.583 214 36 550 0.544 0.0122 cyclic delta REC 35 0.583 213 36 559 0.543 0.0124 cyclic delta REC 36 0.583 213 36 839 0.544 0.0186 cyclic delta REC 37 0.583 213 36 1093 0.543 0.0242 cyclic delta REC 38 0.583 213 36 1221 0.544 0.0271 REC 39 0.582 213 36 1481 0.544 0.0327 REC 40 0.582 213 36 1629 0.544 0.0360 REC 41 0.583 214 37 1896 0.546 0.0422 REC 42 0.583 214 37 2049 0.545 0.0455 REC 43 0.583 214 37 545 0.545 0.0120 (1) Set cyclic for zero flapping then apply delta control; nominal fwd flt ref point Run TR092RN080 continued Point Data Rotor VKTS Coll., Thrust, Notes 𝜇 C / 𝜎 T Type Point RPM/ deg lb M tip REC 44 0.581 214 38 512 0.156 0.0106 REC 45 0.581 214 38 2618 0.031 0.0542 REC 46 0.584 214 36 354 0.038 0.0437 REC 47 0.583 62 10 413 0.000 0.0501 nominal fwd - flight ref. point REC 48 0.583 12 5 2623 0.026 0.0542 hover ref. point REC 49 201 6 5 975 0.157 0.0203 REC 50 SIM 0 5 static REC 51 SIM 15 static ZER 52 SIM 15 CAL 53 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN081 8/17/2018 Airplane forward flight, operator training, 0 deg yaw, 240 - 270 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 0 SIM CAL 2 0 SIM ZER 3 0 SIM CAL 4 0 SIM ZER 5 0 SIM CAL 6 0 SIM REC 7 0 SIM REC 8 0 SIM REC 9 0 4 200 416 0.024 0.0496 Rotating ref. point REC 10 0 13 0.583 2596 0.032 0.0537 Airplane mode rpm ref. point REC 11 0 61 0.583 493 0.156 0.0103 Operating Training Points - Loaded Rate Check REC 12 0 61 0.582 516 0.156 0.0107 cyclic delta (Rate 2) REC 13 0 61 0.582 509 0.156 0.0106 cyclic delta (Rate 2) REC 14 0 241 0.582 607 0.621 0.0137 Record initial cyclic settings before input REC 15 0 241 0.582 575 0.621 0.0130 cyclic delta from 0 - flapping trim REC 16 0 241 0.582 628 0.619 0.0142 cyclic delta REC 17 0 240 0.581 575 0.618 0.0130 cyclic delta REC 18 0 241 0.582 676 0.619 0.0153 cyclic delta REC 19 0 241 0.583 598 0.618 0.0135 cyclic delta REC 20 0 240 0.582 642 0.617 0.0145 cyclic delta REC 21 0 241 0.581 570 0.618 0.0129 cyclic delta REC 22 0 242 0.582 607 0.619 0.0137 cyclic delta REC 23 0 242 0.582 779 0.620 0.0176 REC 24 0 242 0.581 1146 0.621 0.0260 REC 25 0 243 0.582 1228 0.624 0.0278 REC 26 0 243 0.583 1517 0.621 0.0341 REC 27 0 243 0.582 1728 0.623 0.0390 REC 28 0 245 0.584 528 0.624 0.0119 REC 29 0 273 0.583 700 0.698 0.0161 REC 30 0 268 0.583 635 0.685 0.0146 REC 31 0 269 0.583 561 0.686 0.0129 cyclic delta REC 32 0 268 0.583 587 0.685 0.0135 cyclic delta REC 33 0 269 0.583 516 0.685 0.0118 cyclic delta REC 34 0 268 0.581 669 0.685 0.0154 cyclic delta REC 35 0 263 0.583 661 0.671 0.0151 Tunnel speed lowered for fan drive BMS limits REC 36 0 264 0.583 867 0.673 0.0198 REC 37 0 265 0.583 1151 0.676 0.0264 REC 38 0 265 0.583 1223 0.676 0.0279 REC 39 0 265 0.582 1533 0.675 0.0351 REC 40 0 SIM static REC 41 0 SIM static ZER 42 0 SIM CAL 43 0 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN083 8/22/2018 Helicopter forward flight, 90 deg yaw Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 SIM REC 10 90 200 448 0.0542 Rotating ref. point REC 11 90 3 0.684 2284 0.007 0.0343 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 12 90 5 0.684 2350 0.010 0.0354 X is established at start of run REC 13 90 200 532 0.0650 REC 14 90 SIM static REC 15 90 SIM static ZER 16 90 SIM CAL 17 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN085 8/27/2018 Helicopter forward flight, 90 deg yaw, 57 & 80 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM (1) CAL 2 90 SIM ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM ZER 7 90 SIM CAL 8 90 SIM REC 9 90 SIM REC 10 90 SIM REC 11 90 4 200 411 0.024 0.0492 Rotating ref. point REC 12 90 8 0.684 2252 0.017 0.0340 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 13 90 57 0.684 1012 0.125 0.0153 Set rpm, then match M ; nominal fwd flight tip ref point REC 14 90 57 0.684 1253 0.125 0.0190 REC 15 90 57 0.684 1948 0.125 0.0296 REC 16 90 57 0.684 2575 0.125 0.0390 REC 17 90 57 0.684 3229 0.125 0.0490 REC 18 90 57 0.683 3191 0.125 0.0484 REC 19 90 57 0.684 3289 0.125 0.0499 cyclic delta from 0 - flapping trim REC 20 90 57 0.684 3268 0.125 0.0495 cyclic delta REC 21 90 57 0.684 3253 0.125 0.0493 cyclic delta REC 22 90 57 0.684 3268 0.125 0.0495 cyclic delta REC 23 90 57 0.684 3217 0.125 0.0488 cyclic delta REC 24 90 57 0.684 3264 0.125 0.0495 cyclic delta REC 25 90 57 0.684 3218 0.125 0.0488 cyclic delta REC 26 90 57 0.683 3254 0.125 0.0494 trim to zero flapping REC 27 90 57 0.684 3839 0.125 0.0582 REC 28 90 57 0.684 4620 0.125 0.0701 REC 29 90 57 0.684 5233 0.125 0.0794 REC 30 90 57 0.683 5880 0.125 0.0892 REC 31 90 57 0.683 6589 0.125 0.1000 REC 32 90 57 0.683 3202 0.125 0.0486 REC 33 90 78 0.684 3899 0.170 0.0593 REC 34 90 80 0.684 3871 0.175 0.0589 trim to zero flapping; establish ref point REC 35 90 80 0.684 3228 0.175 0.0492 trim to zero flapping; establish ref point REC 36 90 57 0.684 1228 0.124 0.0186 REC 37 90 8 0.683 2434 0.016 0.0368 X is established at start of run REC 38 90 0 200 523 0.000 0.0634 REC 39 90 SIM static REC 40 90 SIM static REC 41 90 SIM ZER 42 90 SIM (1) True setting on MSS is 90.3 to get TTR at 90 deg relative to tunnel Table 7. TTR/699 Run Log (continued) Run TR092RN086 8/28/2018 Conversion forward flight, thrust sweeps, 90 & 75 deg yaw, 57 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM (1) CAL 2 90 SIM ZER 3 90 SIM CAL 4 90 SIM AB ZER 5 90 SIM CAL 6 90 SIM Manual AB on select channels ZER 7 90 SIM CAL 8 90 SIM ZER 9 90 SIM CAL 10 90 SIM REC 11 90 SIM Forgot to hit take data switch REC 12 90 SIM REC 13 90 SIM REC 14 90 3.6 200 434 0.022 0.0518 Rotating ref. point REC 15 90 8.2 569 2251 0.018 0.0339 Helicopter mode rpm; min thrust, high blade loads - recirculation REC 16 90 56.7 0.684 3214 0.124 0.0487 Set rpm, then match M ; nominal fwd flight tip ref point REC 17 90 56.8 0.663 3064 0.128 0.0493 RPM sweep, hub acceleration - do not change collective, retrim flap REC 18 90 57.4 0.684 3230 0.125 0.0489 REC 19 85 57.6 0.684 3244 0.126 0.0491 REC 20 80 57.6 0.684 3224 0.126 0.0488 REC 21 75 57.8 0.684 3210 0.126 0.0486 REC 22 70 57.8 0.684 3190 0.126 0.0483 REC 23 75 56.9 0.684 659 0.124 0.0100 REC 24 75 57.1 0.684 1274 0.124 0.0193 REC 25 75 57.2 0.684 1938 0.125 0.0293 REC 26 75 57.3 0.683 2593 0.125 0.0393 REC 27 75 57.6 0.683 3212 0.126 0.0487 REC 28 75 57.7 0.684 3881 0.126 0.0588 REC 29 75 57.9 0.684 4583 0.126 0.0694 REC 30 75 58.2 0.684 5204 0.127 0.0788 REC 31 75 58.3 0.684 5900 0.127 0.0894 REC 32 75 57.6 0.684 6551 0.125 0.0992 Max thrust REC 33 75 57.7 0.684 7195 0.126 0.1090 REC 34 75 57.9 0.684 7867 0.126 0.1191 lost gages around here REC 35 75 56.8 0.683 3242 0.124 0.0491 return to ref condition REC 36 90 57.7 0.684 3224 0.126 0.0488 REC 37 90 6.8 0.684 2389 0.015 0.0360 REC 38 90 0.9 201 512 0.005 0.0623 sofdas stopped at 12:08 REC 39 90 0 SIM static REC 40 90 0 SIM static ZER 41 90 0 SIM CAL 42 90 0 SIM (1) True setting on MSS is 90.3 to get TTR at 90 deg relative to tunnel Table 7. TTR/699 Run Log (continued) Run TR092RN087 8/29/2018 Conversion forward flight, thrust sweeps, 75 deg yaw, 57, 70, 81, 92 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90.3 SIM CAL 2 90.3 SIM ZER 3 90.3 SIM CAL 4 90.3 SIM AB ZER 5 90.3 SIM CAL 6 90.3 SIM ZER 7 90.3 SIM CAL 8 90.3 SIM REC 9 90.3 0 SIM 0 0 0 REC 10 90.3 0 SIM 0 0 0 REC 11 90 0 200 455 0.0556 Rotating ref. point REC 12 90 2 0.684 2400 0.005 0.0362 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 13 90 58 0.684 3222 0.125 0.0488 Set rpm, then match M ; nominal fwd flight tip ref point REC 14 75 58 0.683 3226 0.126 0.0489 REC 15 75 70 0.684 3193 0.151 0.0485 REC 16 75 69 0.683 541 0.149 0.0082 Min CTOS - trim to zero flapping REC 17 75 69 0.684 1259 0.150 0.0191 REC 18 75 69 0.684 1922 0.150 0.0292 REC 19 75 69 0.683 2505 0.150 0.0381 REC 20 75 69 0.684 3239 0.150 0.0492 REC 21 75 70 0.684 3893 0.151 0.0591 REC 22 75 70 0.684 4521 0.151 0.0687 REC 23 75 70 0.684 5239 0.151 0.0795 REC 24 75 70 0.684 5916 0.151 0.0898 REC 25 75 70 0.684 6490 0.151 0.0986 REC 26 75 70 0.684 7117 0.151 0.1081 REC 27 75 70 0.684 7775 0.152 0.1180 Max CTOS REC 28 75 70 0.684 3223 0.150 0.0489 return to ref condition REC 29 75 81 0.684 3145 0.175 0.0478 REC 30 75 81 0.684 3176 0.175 0.0483 cyclic delta from 0 - flapping trim REC 31 75 81 0.684 3199 0.175 0.0487 cyclic delta REC 32 75 81 0.684 3139 0.175 0.0478 cyclic delta REC 33 75 81 0.684 3086 0.175 0.0470 cyclic delta REC 34 75 81 0.684 3173 0.175 0.0483 cyclic delta REC 35 75 81 0.684 3144 0.175 0.0478 cyclic delta REC 36 75 81 0.684 3155 0.175 0.0480 REC 37 75 81 0.684 3140 0.175 0.0478 REC 38 75 81 0.684 551 0.175 0.0084 Min CTOS - trim to zero flapping REC 39 75 81 0.684 1211 0.175 0.0184 REC 40 75 81 0.684 1917 0.175 0.0292 REC 41 75 81 0.684 2519 0.175 0.0383 REC 42 75 81 0.684 3135 0.175 0.0478 REC 43 75 81 0.684 3763 0.175 0.0573 REC 44 75 81 0.684 4435 0.175 0.0675 REC 45 75 81 0.684 5159 0.175 0.0785 REC 46 75 81 0.684 5754 0.175 0.0876 Run TR092RN087 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 47 75 81 0.684 6409 0.175 0.0976 REC 48 75 81 0.684 7084 0.176 0.1077 REC 49 75 81 0.684 7727 0.176 0.1177 Max CTOS REC 50 75 81 0.684 3203 0.176 0.0488 return to ref condition REC 51 75 93 0.684 3135 0.200 0.0479 REC 52 75 92 0.684 396 0.199 0.0060 Min CTOS - trim to zero flapping REC 53 75 92 0.684 1152 0.199 0.0176 REC 54 75 92 0.684 1834 0.200 0.0280 REC 55 75 93 0.684 2530 0.200 0.0387 REC 56 75 92 0.683 3098 0.200 0.0474 REC 57 75 93 0.684 3638 0.201 0.0555 REC 58 75 93 0.684 4451 0.201 0.0679 REC 59 75 93 0.684 5013 0.201 0.0765 REC 60 75 92 0.684 5702 0.200 0.0871 REC 61 75 92 0.684 6384 0.200 0.0975 REC 62 75 93 0.684 7026 0.200 0.1072 Max CTOS REC 63 75 92 0.684 3150 0.200 0.0481 REC 64 75 58 0.684 3235 0.125 0.0491 REC 65 90 58 0.684 3176 0.126 0.0481 REC 66 90 6 0.684 2296 0.012 0.0346 REC 67 90 1 200 468 0.003 0.0580 REC 68 90.3 0 SIM static REC 69 90.3 SIM static ZER 70 90.3 SIM CAL 71 90.3 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN088 8/30/2018 Conversion forward flight, thrust sweeps, 75 deg yaw, 104 & 115 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 4 201 474 0.028 0.0566 Rotating ref. point REC 10 90 8 0.684 2424 0.017 0.0364 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 57 0.684 3212 0.125 0.0485 Set rpm, then match M ; nominal fwd flight tip ref point REC 12 75 57 0.684 3234 0.126 0.0488 REC 13 75 103 0.684 3034 0.225 0.0463 REC 14 75 102 0.684 457 0.224 0.0070 Min CTOS - trim to zero flapping REC 15 75 103 0.684 1214 0.225 0.0185 REC 16 75 103 0.684 1724 0.225 0.0263 REC 17 75 103 0.684 2466 0.225 0.0376 REC 18 75 103 0.684 3196 0.225 0.0487 REC 19 75 103 0.684 3776 0.226 0.0576 REC 20 75 104 0.684 4330 0.226 0.0660 REC 21 75 103 0.684 5033 0.226 0.0768 REC 22 75 104 0.684 5663 0.226 0.0864 REC 23 75 104 0.684 6393 0.226 0.0976 REC 24 75 103 0.684 6969 0.225 0.1063 Max CTOS REC 25 75 103 0.684 3034 0.225 0.0462 return to ref condition REC 26 75 115 0.684 4237 0.250 0.0648 REC 27 75 115 0.684 4992 0.250 0.0764 REC 28 75 115 0.684 5594 0.251 0.0855 REC 29 75 115 0.684 6335 0.251 0.0969 Max CTOS REC 30 75 115 0.684 4264 0.250 0.0653 return to ref condition REC 31 75 57 0.684 3135 0.125 0.0473 REC 32 90 58 0.684 3188 0.125 0.0480 REC 33 90 7 0.684 2371 0.015 0.0356 REC 34 90 4 200 497 0.024 0.0603 REC 35 90 SIM 135 static REC 36 90 SIM static ZER 37 90 SIM CAL 38 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN089 8/30/2018 Conversion forward flight, thrust sweeps, 60 deg yaw, 70 & 81 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM Manual AB ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 0 200 458 0.000 0.0560 Rotating ref. point REC 10 90 7 0.684 2530 0.015 0.0381 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 58 0.684 3212 0.125 0.0485 Set rpm, then match M ; nominal fwd flight tip ref point REC 12 60 58 0.684 3309 0.125 0.0500 REC 13 60 58 0.684 3332 0.125 0.0504 Added Ref Point Turntable at 60.2 deg REC 14 60 70 0.684 3220 0.151 0.0487 Cyclic ref REC 15 60 69 0.684 3239 0.151 0.0490 cyclic delta from 0 - flapping trim REC 16 60 69 0.684 3211 0.151 0.0486 cyclic delta REC 17 60 69 0.684 3272 0.151 0.0495 cyclic delta REC 18 60 69 0.684 3204 0.151 0.0485 cyclic delta REC 19 60 69 0.684 3157 0.151 0.0478 cyclic delta REC 20 60 69 0.684 3215 0.150 0.0487 cyclic delta REC 21 60 69 0.684 3178 0.151 0.0481 cyclic delta REC 22 60 69 0.684 3266 0.151 0.0495 REC 23 60 69 0.684 549 0.150 0.0083 Min CTOS - trim to zero flapping REC 24 60 69 0.684 1281 0.150 0.0194 REC 25 60 70 0.684 1906 0.151 0.0289 REC 26 60 69 0.684 2624 0.150 0.0398 REC 27 60 69 0.683 3166 0.151 0.0480 REC 28 60 69 0.684 3878 0.151 0.0588 REC 29 60 69 0.684 4616 0.150 0.0699 REC 30 60 69 0.684 5216 0.150 0.0790 REC 31 60 70 0.684 5881 0.151 0.0891 REC 32 60 70 0.684 6513 0.151 0.0986 REC 33 60 69 0.684 7195 0.151 0.1089 REC 34 60 70 0.684 7803 0.151 0.1181 Max CTOS REC 35 60 69 0.684 3243 0.150 0.0491 return to ref condition REC 36 60 81 0.684 3218 0.175 0.0488 REC 37 60 81 0.684 511 0.176 0.0078 Min CTOS - trim to zero flapping REC 38 60 80 0.684 1186 0.174 0.0180 REC 39 60 81 0.684 1901 0.175 0.0289 REC 40 60 81 0.684 2620 0.176 0.0398 REC 41 60 81 0.684 3182 0.176 0.0483 REC 42 60 81 0.684 3766 0.175 0.0571 REC 43 60 81 0.684 4483 0.176 0.0681 REC 44 60 81 0.684 5172 0.175 0.0785 REC 45 60 81 0.684 5827 0.175 0.0885 REC 46 60 81 0.684 6463 0.175 0.0981 Run TR092RN087 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 47 60 81 0.684 7059 0.176 0.1072 Max CTOS REC 48 60 81 0.684 3161 0.176 0.0480 return to ref condition REC 49 60 57 0.684 3235 0.124 0.0489 REC 50 90 58 0.684 3187 0.125 0.0482 REC 51 90 6 0.684 2310 0.013 0.0348 REC 52 90 2 201 506 0.011 0.0620 REC 53 90 SIM static REC 54 90 SIM static ZER 55 90 SIM CAL 56 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN090 8/31/2018 Conversion forward flight, thrust sweeps, 60 & 45 deg yaw, 91 - 126 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 2 200 501 0.011 0.0593 Rotating ref. point REC 10 90 7 0.684 2276 0.014 0.0342 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 57 0.684 3312 0.126 0.0500 Set rpm, then match M ; nominal fwd flight tip ref point REC 12 60 57 0.684 3273 0.125 0.0494 REC 13 60 91 0.684 3252 0.200 0.0495 REC 14 60 92 0.684 515 0.201 0.0078 Min CTOS - trim to zero flapping REC 15 60 92 0.684 1215 0.201 0.0185 REC 16 60 92 0.684 1846 0.202 0.0281 REC 17 60 91 0.684 2614 0.200 0.0397 REC 18 60 91 0.684 3149 0.200 0.0479 REC 19 60 91 0.684 3915 0.200 0.0596 REC 20 60 92 0.684 4474 0.201 0.0680 REC 21 60 92 0.684 5151 0.201 0.0783 REC 22 60 91 0.684 5910 0.200 0.0900 REC 23 60 91 0.684 6475 0.200 0.0984 Max CTOS REC 24 60 91 0.684 3276 0.200 0.0498 return to ref condition REC 25 60 103 0.684 3147 0.226 0.0480 REC 26 60 103 0.684 1800 0.225 0.0275 cyclic delta from 0 - flapping trim REC 27 60 103 0.684 1879 0.225 0.0287 cyclic delta REC 28 60 103 0.684 1876 0.225 0.0287 cyclic delta REC 29 60 103 0.684 1829 0.225 0.0279 cyclic delta REC 30 60 103 0.684 1856 0.225 0.0284 cyclic delta REC 31 60 103 0.684 1854 0.225 0.0283 cyclic delta REC 32 60 103 0.684 1832 0.225 0.0280 cyclic delta REC 33 60 103 0.684 1926 0.225 0.0294 cyclic delta REC 34 60 103 0.684 1903 0.225 0.0291 REC 35 60 103 0.684 489 0.225 0.0075 Min CTOS - trim to zero flapping REC 36 60 103 0.684 1200 0.225 0.0183 REC 37 60 103 0.684 1795 0.226 0.0274 REC 38 60 103 0.683 2563 0.226 0.0392 REC 39 60 103 0.684 3242 0.225 0.0495 REC 40 60 103 0.684 3752 0.225 0.0573 REC 41 60 103 0.684 4191 0.225 0.0640 Max CTOS REC 42 60 103 0.684 1909 0.225 0.0291 return to ref condition REC 43 60 115 0.684 1732 0.251 0.0265 REC 44 60 114 0.684 570 0.250 0.0087 Min CTOS - trim to zero flapping REC 45 60 114 0.684 1185 0.250 0.0181 REC 46 60 115 0.684 1760 0.250 0.0269 Run TR092RN090 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 47 60 115 0.684 2472 0.251 0.0379 REC 48 60 115 0.683 3182 0.251 0.0489 Max CTOS REC 49 60 114 0.684 1843 0.250 0.0282 return to ref condition REC 50 60 126 0.684 1767 0.275 0.0272 REC 51 60 126 0.684 518 0.275 0.0080 Min CTOS - trim to zero flapping REC 52 60 126 0.684 1142 0.275 0.0176 REC 53 60 126 0.683 1677 0.275 0.0259 REC 54 60 126 0.684 2443 0.276 0.0376 Max CTOS, missed CTOS of 0.05 look at SOF PN36 - >37 REC 55 60 126 0.684 1711 0.275 0.0263 return to ref condition REC 56 60 58 0.684 3232 0.125 0.0488 REC 57 45 57 0.684 3284 0.125 0.0496 REC 58 45 92 0.684 3194 0.200 0.0486 REC 59 45 92 0.684 3208 0.200 0.0488 cyclic delta from 0 - flapping trim REC 60 45 92 0.684 3203 0.200 0.0488 cyclic delta REC 61 45 91 0.684 3192 0.199 0.0486 cyclic delta REC 62 45 92 0.684 3208 0.200 0.0489 cyclic delta REC 63 45 92 0.683 3213 0.200 0.0490 cyclic delta REC 64 45 92 0.684 3187 0.200 0.0486 cyclic delta REC 65 45 92 0.684 3177 0.200 0.0483 cyclic delta REC 66 45 92 0.684 3172 0.200 0.0483 REC 67 45 92 0.684 531 0.200 0.0081 Min CTOS - trim to zero flapping REC 68 45 92 0.685 1250 0.200 0.0190 REC 69 45 92 0.684 1823 0.201 0.0277 REC 70 45 92 0.684 2523 0.200 0.0384 REC 71 45 92 0.684 3214 0.201 0.0490 REC 72 45 92 0.684 3845 0.201 0.0586 REC 73 45 92 0.684 4520 0.202 0.0689 REC 74 45 92 0.683 5174 0.200 0.0789 REC 75 45 92 0.684 5819 0.200 0.0887 REC 76 45 92 0.683 6535 0.201 0.0997 Max CTOS REC 77 45 92 0.684 3136 0.200 0.0477 return to ref condition REC 78 45 58 0.684 3187 0.125 0.0481 REC 79 90 57 0.684 3293 0.125 0.0498 REC 80 90 5 0.684 2313 0.011 0.0348 REC 81 90 0 201 510 0.000 0.0620 REC 82 90 SIM static REC 83 90 SIM static ZER 84 90 SIM CAL 85 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN091 9/4/2018 Conversion forward flight, thrust sweeps, 45 deg yaw, 57, 103, 115 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 4 201 456 0.022 0.0543 Rotating ref. point REC 10 90 7 0.685 2303 0.016 0.0347 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 57 0.684 3266 0.125 0.0496 Set rpm, then match M ; nominal fwd flight ref tip point REC 12 45 57 0.684 3313 0.125 0.0503 REC 13 45 57 0.683 3262 0.125 0.0496 cyclic delta from 0 - flapping trim REC 14 45 57 0.684 3300 0.125 0.0501 cyclic delta REC 15 45 103 0.684 3143 0.225 0.0482 REC 16 45 103 0.684 675 0.225 0.0104 Min CTOS - trim to zero flapping REC 17 45 103 0.684 1240 0.225 0.0190 REC 18 45 103 0.684 1975 0.225 0.0303 REC 19 45 103 0.683 2527 0.225 0.0389 REC 20 45 103 0.684 3229 0.225 0.0496 REC 21 45 103 0.683 3927 0.225 0.0604 REC 22 45 103 0.684 4458 0.225 0.0684 REC 23 45 103 0.684 5124 0.226 0.0788 Max CTOS REC 24 45 103 0.684 3192 0.225 0.0490 return to ref condition REC 25 45 114 0.684 3194 0.250 0.0492 REC 26 45 115 0.684 593 0.250 0.0091 Min CTOS - trim to zero flapping REC 27 45 114 0.684 1295 0.250 0.0199 REC 28 45 115 0.684 1811 0.251 0.0279 REC 29 45 115 0.684 2665 0.252 0.0411 REC 30 45 115 0.684 3117 0.252 0.0481 REC 31 45 115 0.684 3886 0.250 0.0599 Max CTOS REC 32 45 115 0.684 3166 0.250 0.0487 return to ref condition REC 33 45 57 0.684 3272 0.125 0.0497 REC 34 90 57 0.684 3230 0.125 0.0490 REC 35 90 3 0.685 2355 0.007 0.0355 REC 36 90 0 201 499 0.000 0.0606 REC 37 90 SIM static REC 38 90 SIM static ZER 39 90 SIM CAL 40 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN092 9/5/2018 Conversion forward flight, thrust sweeps, 90 deg yaw Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM REC 5 90 SIM REC 6 90 SIM REC 7 90 5 201 453 0.028 0.0539 Rotating ref. point REC 8 90 7 0.684 2425 0.016 0.0365 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 9 90 6 0.684 2311 0.013 0.0348 REC 10 90 4 201 471 0.024 0.0562 REC 11 90 SIM static REC 12 90 SIM static ZER 13 90 SIM CAL 14 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN093 9/5/2018 Conversion forward flight, thrust sweeps, 30 & 45 deg yaw, 57 - 138 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 0 201 445 0.000 0.0537 Rotating ref. point REC 10 90 4 0.684 2231 0.009 0.0336 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 57 0.684 3212 0.125 0.0486 Set rpm, then match M ; nominal fwd flight tip ref point REC 12 45 58 0.684 3284 0.125 0.0498 REC 13 45 127 0.684 1952 0.276 0.0301 REC 14 45 127 0.683 1788 0.276 0.0276 cyclic delta from 0 - flapping trim REC 15 45 127 0.683 1896 0.276 0.0293 cyclic delta REC 16 45 127 0.684 1883 0.275 0.0291 cyclic delta REC 17 45 127 0.684 1863 0.275 0.0287 cyclic delta REC 18 45 127 0.684 1879 0.276 0.0290 cyclic delta REC 19 45 127 0.685 1841 0.275 0.0283 cyclic delta REC 20 45 127 0.685 1855 0.275 0.0285 cyclic delta REC 21 45 127 0.685 1873 0.275 0.0288 REC 22 45 126 0.684 591 0.274 0.0091 Min CTOS - trim to zero flapping REC 23 45 126 0.684 1245 0.275 0.0192 REC 24 45 127 0.683 1866 0.275 0.0289 REC 25 45 127 0.683 2595 0.277 0.0402 REC 26 45 127 0.683 3096 0.277 0.0479 Max CTOS REC 27 45 127 0.683 1884 0.276 0.0291 return to ref condition REC 28 45 137 0.684 601 0.298 0.0093 Min CTOS - trim to zero flapping REC 29 45 138 0.684 1261 0.299 0.0196 REC 30 45 138 0.683 1821 0.300 0.0283 Max CTOS REC 31 45 137 0.684 533 0.299 0.0083 return to ref condition REC 32 45 57 0.684 3283 0.124 0.0497 REC 33 30 58 0.684 3312 0.125 0.0502 REC 34 30 104 0.684 1925 0.225 0.0295 REC 35 30 104 0.684 1942 0.225 0.0298 cyclic delta REC 36 30 104 0.684 1963 0.225 0.0301 cyclic delta REC 37 30 104 0.684 1985 0.226 0.0304 cyclic delta REC 38 30 104 0.683 1933 0.226 0.0297 cyclic delta REC 39 30 104 0.684 1883 0.226 0.0289 cyclic delta REC 40 30 104 0.684 1941 0.226 0.0298 cyclic delta REC 41 30 104 0.684 1894 0.226 0.0290 cyclic delta REC 42 30 104 0.684 1982 0.226 0.0304 REC 43 30 104 0.684 746 0.226 0.0114 Min CTOS - trim to zero flapping REC 44 30 104 0.684 1329 0.225 0.0204 REC 45 30 104 0.684 1968 0.225 0.0302 REC 46 30 103 0.684 2586 0.225 0.0396 Run TR092RN093 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 47 30 104 0.684 3277 0.226 0.0502 REC 48 30 104 0.684 3860 0.226 0.0592 REC 49 30 104 0.684 4658 0.225 0.0714 REC 50 30 104 0.683 5213 0.226 0.0800 REC 51 30 104 0.683 5654 0.226 0.0869 Max CTOS REC 52 30 104 0.684 1926 0.225 0.0295 return to ref condition REC 53 30 115 0.684 1927 0.251 0.0297 REC 54 30 115 0.684 1275 0.250 0.0196 REC 55 30 115 0.684 617 0.249 0.0095 Min CTOS - trim to zero flapping REC 56 30 115 0.684 1321 0.250 0.0203 REC 57 30 115 0.684 1889 0.250 0.0290 REC 58 30 116 0.684 2550 0.251 0.0393 REC 59 30 115 0.684 3292 0.249 0.0506 REC 60 30 115 0.684 3874 0.250 0.0596 REC 61 30 115 0.684 4632 0.251 0.0713 REC 62 30 116 0.684 5189 0.251 0.0799 Max CTOS REC 63 30 115 0.685 2009 0.250 0.0308 return to ref condition REC 64 30 127 0.685 1976 0.275 0.0305 REC 65 30 127 0.685 694 0.275 0.0107 Min CTOS - trim to zero flapping REC 66 30 127 0.684 1360 0.275 0.0210 REC 67 30 126 0.684 1967 0.275 0.0304 REC 68 30 127 0.684 2643 0.275 0.0409 REC 69 30 127 0.684 3192 0.276 0.0493 REC 70 30 127 0.684 3811 0.275 0.0589 REC 71 30 127 0.683 4535 0.276 0.0702 REC 72 30 127 0.683 4812 0.275 0.0745 Max CTOS REC 73 30 127 0.685 1808 0.275 0.0279 return to ref condition REC 74 30 58 0.684 3309 0.125 0.0502 REC 75 90 58 0.684 3225 0.125 0.0489 REC 76 90 7 0.684 2281 0.015 0.0344 REC 77 90 0 201 529 0.002 0.0648 REC 78 90 SIM static REC 79 90 SIM static ZER 80 90 SIM CAL 81 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN094 9/6/2018 Conversion forward flight, thrust sweeps, 30 & 80 deg yaw, 57 - 160 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM REC 5 90 SIM REC 6 90 SIM REC 7 90 4 201 478 0.026 0.0566 Rotating ref. point REC 8 90 8 0.684 2450 0.017 0.0368 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 9 90 57 0.683 3198 0.126 0.0483 Set rpm, then match M ; nominal fwd flight tip ref point REC 10 30 57 0.684 3285 0.125 0.0496 REC 11 30 137 0.684 1927 0.300 0.0297 REC 12 30 137 0.683 1961 0.301 0.0303 cyclic delta from 0 - flapping trim REC 13 30 137 0.683 1860 0.301 0.0288 cyclic delta REC 14 30 137 0.683 1818 0.301 0.0281 cyclic delta REC 15 30 137 0.683 1935 0.301 0.0299 cyclic delta REC 16 30 137 0.683 1858 0.301 0.0288 cyclic delta REC 17 30 137 0.684 1856 0.301 0.0287 cyclic delta REC 18 30 137 0.683 1867 0.300 0.0289 cyclic delta REC 19 30 137 0.683 1919 0.300 0.0297 REC 20 30 137 0.684 590 0.300 0.0091 Min CTOS - trim to zero flapping REC 21 30 137 0.684 1349 0.300 0.0208 REC 22 30 137 0.684 1943 0.300 0.0300 REC 23 30 137 0.684 2622 0.300 0.0404 REC 24 30 137 0.684 3195 0.301 0.0493 REC 25 30 138 0.684 3852 0.302 0.0595 REC 26 30 137 0.683 4302 0.300 0.0665 Max CTOS REC 27 30 138 0.684 2018 0.301 0.0311 return to ref condition REC 28 30 149 0.685 1890 0.325 0.0292 REC 29 30 148 0.684 516 0.325 0.0080 Min CTOS - trim to zero flapping REC 30 30 149 0.684 1315 0.325 0.0204 REC 31 30 149 0.684 1951 0.325 0.0303 REC 32 30 149 0.684 2590 0.326 0.0402 REC 33 30 149 0.684 3008 0.326 0.0467 Max CTOS REC 34 30 149 0.684 2015 0.325 0.0313 return to ref condition REC 35 30 160 0.684 603 0.350 0.0094 Min CTOS - trim to zero flapping REC 36 30 160 0.684 1326 0.350 0.0207 REC 37 30 160 0.684 1647 0.351 0.0257 Max CTOS REC 38 30 160 0.684 1299 0.350 0.0203 REC 39 30 57 0.684 3301 0.125 0.0498 REC 40 80 58 0.684 3191 0.125 0.0481 REC 41 80 58 0.684 3252 0.125 0.0490 cyclic delta REC 42 80 58 0.685 3279 0.125 0.0494 cyclic delta REC 43 80 58 0.685 3273 0.125 0.0493 cyclic delta REC 44 80 57 0.684 3189 0.125 0.0480 cyclic delta REC 45 80 57 0.684 3184 0.125 0.0480 cyclic delta REC 46 80 57 0.684 3217 0.125 0.0485 cyclic delta Run TR092RN0 94 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 47 80 57 0.685 3127 0.125 0.0471 cyclic delta REC 48 80 57 0.684 3156 0.125 0.0475 REC 49 80 57 0.684 672 0.125 0.0101 Min CTOS - trim to zero flapping REC 50 80 57 0.684 1240 0.125 0.0187 REC 51 80 58 0.684 1840 0.125 0.0278 REC 52 80 57 0.684 2498 0.125 0.0377 REC 53 80 57 0.684 3206 0.125 0.0483 REC 54 80 58 0.684 3833 0.125 0.0577 REC 55 80 57 0.684 4580 0.125 0.0690 REC 56 80 57 0.685 5254 0.125 0.0791 REC 57 80 57 0.684 5514 0.125 0.0831 Max CTOS REC 58 80 58 0.685 3196 0.125 0.0481 return to ref condition REC 59 90 57 0.684 3183 0.125 0.0480 REC 60 90 5 0.683 2414 0.011 0.0363 REC 61 90 0 201 515 0.000 0.0623 REC 62 90 SIM static REC 63 90 SIM static ZER 64 90 SIM CAL 65 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN095 9/6/2018 Conversion forward flight, thrust sweep, 90 deg yaw, 57 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 0 201 457 0.000 0.0551 Rotating ref. point REC 10 90 5 0.684 2406 0.012 0.0362 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 58 0.684 3211 0.126 0.0484 Set rpm, then match M ; nominal fwd flight tip ref point REC 12 90 58 0.684 1533 0.125 0.0232 Min CTOS - trim to zero flapping REC 13 90 57 0.684 1905 0.125 0.0288 REC 14 90 57 0.684 2574 0.125 0.0389 REC 15 90 57 0.684 3226 0.125 0.0487 REC 16 90 57 0.684 3828 0.125 0.0578 REC 17 90 57 0.684 4548 0.125 0.0686 REC 18 90 57 0.684 5248 0.125 0.0792 REC 19 90 57 0.684 5546 0.125 0.0837 Max CTOS; high loads on swashplate driver REC 20 90 57 0.684 3232 0.125 0.0488 return to ref condition REC 21 90 5 0.683 2398 0.011 0.0361 REC 22 90 0 201 549 0.000 0.0664 REC 23 90 SIM static REC 24 90 SIM static ZER 25 90 SIM CAL 26 90 SIM Table 7. TTR/699 Run Log (continued) Run R092RN099 11/6/2018 Motor checkout (both fwd motors), wind off Air Exchange Open 100%, Louver 7 Open, VS 6 in 80x Mode, VS 4 Closed, VS 3 Open Point Data Yaw, VKTS Rotor Coll., Thrust, Motor Notes C / 𝜎 T Type Point deg RPM deg lb Current (1) ZER 1 0 SIM CAL 2 0 SIM AB ZER 3 0 SIM CAL 4 0 SIM ZER 5 0 SIM CAL 6 0 SIM ZER 7 0 SIM CAL 8 0 SIM REC 9 0 SIM REC 10 0 SIM REC 11 0 0 200 5.0 403 0.0495 REC 12 0 15 571 5.0 3562 0.0537 200 REC 13 0 21 571 10.0 6254 0.0945 300 REC 14 0 24 570 13.1 8124 0.1229 400 REC 15 0 27 570 15.6 9527 0.1445 500 REC 16 0 27 569 16.6 10191 0.1549 550 REC 17 0 16 572 5.0 3505 0.0528 REC 18 0 8 200 5.0 265 0.0325 200 REC 19 0 static; bad point REC 20 0 SIM REC 21 0 SIM static ZER 22 0 SIM CAL 23 0 SIM (1) New trunnion etc. in rotating scissor Table 7. TTR/699 Run Log (continued) Run R092RN100 11/6/2018 Motor checkout (port motor disconnected, running motor 5 only) Air Exchange Open 100%, Louver 7 Open, VS 6 in 80x Mode, VS 4 Closed, VS 3 Open Point Data Yaw, VKTS Rotor Coll., Thrust, Motor Notes C / 𝜎 T Type Point deg RPM deg lb Current ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 ZER 5 0 SIM 15 CAL 6 0 SIM 15 ZER 7 0 SIM 15 CAL 8 0 SIM 15 REC 9 0 SIM 15 REC 10 0 SIM 5 REC 11 0 0 200 5.0 447 0.0551 REC 12 0 9 573 - 0.7 1306 0.0194 200 REC 13 0 14 572 4.6 3447 0.0514 300 REC 14 0 17 572 7.2 4746 0.0709 400 REC 15 0 20 570 9.1 5798 0.0873 500 REC 16 0 21 569 9.9 6270 0.0946 550 REC 17 0 SIM 5 REC 18 0 SIM 15 static ZER 19 0 SIM 15 CAL 20 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN101 11/7/2018 NFAC configuration effects, thrust sweep, 0 deg yaw, 569 rpm, wind off Air Exchange Open 100%, Louver 7 Open, VS 6 in 80x Mode, VS 4 Closed, VS 3 Open Point Data Yaw, VKTS Rotor Coll., Thrust, Notes C / 𝜎 T Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 ZER 5 0 SIM 15 CAL 6 0 SIM 15 ZER 7 0 SIM 15 CAL 8 0 SIM 15 ZER 9 0 SIM 15 CAL 10 0 SIM 15 REC 11 0 SIM 15 static REC 12 0 200 5 static REC 13 0 0 200 5 436 0.0508 REC 14 0 15 558 5 3488 0.0523 REC 15 0 20 558 7 4385 0.0658 REC 16 0 22 557 9 5360 0.0805 REC 17 0 25 558 11 6563 0.0986 REC 18 0 27 557 13 7726 0.1163 REC 19 0 28 557 14 8344 0.1257 REC 20 0 30 559 15 8987 0.1347 REC 21 0 30 558 16 9699 0.1457 REC 22 0 29 559 15 8977 0.1345 REC 23 0 29 559 14 8414 0.1261 REC 24 0 28 559 13 7749 0.1162 REC 25 0 26 559 11 6538 0.0981 REC 26 0 23 559 9 5401 0.0809 REC 27 0 20 559 7 4360 0.0654 REC 28 0 18 559 5 3356 0.0503 REC 29 0 8 200 5 297 0.0346 REC 30 0 SIM 5 static REC 31 0 SIM 15 static ZER 32 0 SIM 15 CAL 33 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN102 11/7/2018 NFAC configuration effects, thrust sweep, 0 deg yaw, 569 & 478 rpm Air Exchange Open 100%, Louver 7 Open, VS 6 in 80x Mode, VS 4 Open, VS 3 Outboard Half Closed Point Data Yaw, VKTS Rotor Coll., Thrust, Notes C / 𝜎 T Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 SIM 15 static REC 6 0 SIM 5 static REC 7 0 0 200 5 475 0.0561 REC 8 0 10 562 5 3795 0.0569 REC 9 0 13 563 7 4865 0.0729 REC 10 0 15 563 9 5901 0.0885 REC 11 0 18 562 11 7114 0.1069 REC 12 0 21 563 13 8418 0.1264 REC 13 0 21 563 14 9035 0.1357 REC 14 0 22 563 15 9620 0.1443 REC 15 0 24 563 16 10114 0.1519 REC 16 0 21 564 15 9756 0.1461 REC 17 0 20 563 14 9103 0.1366 REC 18 0 20 564 13 8480 0.1271 REC 19 0 17 564 11 7245 0.1087 REC 20 0 16 564 9 5991 0.0898 REC 21 0 13 564 7 4934 0.0740 REC 22 0 11 564 5 3773 0.0566 REC 23 0 8 481 5 2709 0.0559 REC 24 0 9 481 7 3491 0.0720 REC 25 0 12 481 9 4307 0.0888 REC 26 0 14 481 11 5169 0.1066 REC 27 0 15 481 13 6068 0.1253 REC 28 0 16 481 14 6456 0.1334 REC 29 0 17 481 15 6880 0.1420 REC 30 0 18 481 16 7375 0.1522 REC 31 0 19 481 17 7767 0.1604 REC 32 0 19 481 18 8247 0.1703 REC 33 0 20 481 19 8701 0.1798 REC 34 0 20 481 20 8904 0.1842 REC 35 0 21 481 19 8589 0.1776 REC 36 0 21 481 18 8128 0.1679 REC 37 0 19 482 17 7720 0.1593 REC 38 0 18 482 16 7410 0.1530 REC 39 0 16 482 15 6989 0.1440 REC 40 0 15 481 14 6585 0.1361 REC 41 0 14 482 13 6121 0.1263 REC 42 0 14 482 11 5174 0.1066 REC 43 0 12 482 9 4299 0.0886 REC 44 0 10 482 7 3499 0.0721 REC 45 0 6 483 5 2806 0.0577 REC 46 0 0 200 5 466 0.0558 REC 47 0 SIM 5 static REC 48 0 SIM 15 static, disregard Acoustic Point, Zero Point taken while they were taking data Run TR092R102 continued Point Data Yaw, VKTS Rotor Coll., Thrust, Notes C / 𝜎 T Type Point deg RPM deg lb ZER 49 0 SIM 15 REC 50 0 SIM 15 Retake of Point 48 for acoustics ZER 51 0 SIM 15 CAL 52 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN103 11/7/2018 NFAC configuration effects, thrust sweep, 0 deg yaw, 569 rpm, wind off Air Exchange Open 100%, Louver 7 Open, VS 6 in 80x Mode, VS 4 Open, VS 3 Outboard ¾ Closed, Doors G, H, I, J, K, L Closed Point Data Yaw, VKTS Rotor Coll., Thrust, Notes C / 𝜎 T Type Point deg RPM deg lb ZER 1 0 SIM 15 CAL 2 0 SIM 15 AB ZER 3 0 SIM 15 CAL 4 0 SIM 15 REC 5 0 SIM 5 REC 6 0 SIM 5 REC 7 0 0 200 5 475 0.0561 static REC 8 0 10 562 7 3795 0.0569 static REC 9 0 0 201 5 483 0.0580 REC 10 0 6 567 5 4017 0.0604 REC 11 0 7 568 7 5215 0.0783 REC 12 0 9 568 9 6393 0.0962 REC 13 0 8 568 11 7714 0.1159 REC 14 0 12 568 13 8780 0.1321 REC 15 0 13 568 14 9419 0.1417 REC 16 0 11 568 13 8885 0.1336 REC 17 0 10 568 11 7621 0.1145 REC 18 0 9 569 9 6333 0.0950 REC 19 0 7 569 7 5179 0.0776 REC 20 0 5 568 5 4064 0.0611 REC 21 0 0 200 5 489 0.0592 REC 22 0 SIM 15 static REC 23 0 SIM 15 static REC 24 0 SIM 15 REC 25 0 SIM 15 Table 7. TTR/699 Run Log (continued) Run TR092RN104 11/8/2018 Airplane forward flight, thrust sweep, 478 rpm, 120 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 0 SIM CAL 2 0 SIM ZER 3 0 SIM CAL 4 0 SIM ZER 5 0 SIM CAL 6 0 SIM ZER 7 0 SIM CAL 8 0 SIM ZER 9 0 SIM CAL 10 0 SIM REC 11 0 0 SIM 7 0.000 0.0001 REC 12 0 0 SIM - 11 0.000 REC 13 0 0 200 438 0.000 0.0515 Rotating ref. point REC 14 0 9 0.583 2678 0.024 0.0552 Airplane mode rpm ref. point (FAILED TUNNEL START) REC 15 0 0 0.608 - 14 0.000 REC 16 0 0 0.244 439 0.000 0.0517 Rotating ref. point REC 17 0 7 0.583 2691 0.019 0.0554 Airplane mode rpm ref. point REC 18 0 61 0.583 466 0.157 0.0096 Set cyclic for zero flapping; nominal fwd flight ref point REC 19 0 120 0.583 507 0.310 0.0107 REC 20 0 120 0.582 506 0.311 0.0107 cyclic input checks REC 21 0 120 0.582 469 0.311 0.0099 REC 22 0 120 0.582 465 0.311 0.0098 REC 23 0 120 0.582 463 0.311 0.0098 REC 24 0 120 0.583 512 0.310 0.0108 REC 25 0 120 0.584 497 0.310 0.0104 REC 26 0 120 0.583 492 0.310 0.0103 REC 27 0 120 0.583 467 0.310 0.0098 REC 28 0 121 0.582 964 0.311 0.0203 REC 29 0 121 0.583 1426 0.311 0.0300 REC 30 0 121 0.583 1945 0.312 0.0409 REC 31 0 121 0.582 2391 0.312 0.0504 REC 32 0 121 0.583 2908 0.311 0.0611 REC 33 0 121 0.583 3332 0.312 0.0701 REC 34 0 122 0.583 3718 0.313 0.0783 Max CTOS, Torque limited REC 35 0 121 0.583 3317 0.312 0.0698 REC 36 0 121 0.584 2872 0.311 0.0603 REC 37 0 121 0.583 2396 0.312 0.0504 REC 38 0 122 0.583 1911 0.312 0.0401 REC 39 0 121 0.584 1392 0.311 0.0292 REC 40 0 121 0.583 924 0.312 0.0194 REC 41 0 121 0.583 511 0.310 0.0108 REC 42 0 61 0.583 477 0.156 0.0099 nominal fwd - flight ref. point REC 43 0 10 0.583 2643 0.024 0.0543 hover ref. point REC 44 0 5 200 321 0.029 0.0385 REC 45 0 0 SIM 12 0.000 0.0002 static REC 46 0 0 SIM - 7 0.000 static Run TR092RN022 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 47 0 SIM CAL 48 0 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN105 11/8/2018 Airplane forward flight, thrust sweeps, 569 rpm, 60, 70, 107, 142 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 0 SIM CAL 2 0 SIM ZER 3 0 SIM CAL 4 0 SIM ZER 5 0 SIM CAL 6 0 SIM ZER 7 0 SIM CAL 8 0 SIM REC 9 0 SIM REC 10 0 SIM REC 11 0 0 200 431 0.000 0.0517 Rotating ref. point REC 12 0 13 0.684 3603 0.029 0.0539 Airplane mode rpm ref. point REC 13 0 61 0.684 661 0.134 0.0099 Set cyclic for zero flapping; nominal fwd flight ref point REC 14 0 61 0.684 1320 0.133 0.0199 REC 15 0 62 0.683 1995 0.134 0.0300 REC 16 0 61 0.684 2674 0.133 0.0402 REC 17 0 61 0.684 3347 0.134 0.0504 REC 18 0 61 0.684 4017 0.133 0.0605 REC 19 0 61 0.684 4670 0.134 0.0703 REC 20 0 61 0.684 5359 0.134 0.0807 REC 21 0 62 0.684 5978 0.134 0.0900 REC 22 0 61 0.684 6738 0.133 0.1014 REC 23 0 62 0.684 7309 0.134 0.1099 REC 24 0 62 0.684 7505 0.134 0.1129 Max CTOS, Torque limited REC 25 0 62 0.684 684 0.134 0.0103 REC 26 0 72 0.684 658 0.157 0.0099 Set cyclic for zero flapping; nominal fwd flight ref point REC 27 0 72 0.684 1320 0.156 0.0199 REC 28 0 72 0.684 2019 0.157 0.0304 REC 29 0 72 0.684 2651 0.156 0.0400 REC 30 0 72 0.684 3314 0.156 0.0500 REC 31 0 72 0.684 4009 0.157 0.0604 REC 32 0 72 0.684 4682 0.156 0.0706 REC 33 0 72 0.684 5321 0.157 0.0802 REC 34 0 72 0.684 5984 0.157 0.0902 REC 35 0 72 0.684 6707 0.156 0.1011 Max CTOS, Torque limited REC 36 0 72 0.684 657 0.157 0.0099 REC 37 0 107 0.684 683 0.233 0.0104 Set cyclic for zero flapping; nominal fwd flight ref point REC 38 0 107 0.684 1329 0.234 0.0202 REC 39 0 107 0.684 2004 0.233 0.0305 REC 40 0 107 0.684 2601 0.234 0.0396 REC 41 0 107 0.684 3363 0.233 0.0512 REC 42 0 107 0.684 3907 0.233 0.0595 REC 43 0 107 0.684 4620 0.234 0.0703 REC 44 0 107 0.684 5083 0.234 0.0773 Max CTOS, Torque limited REC 45 0 107 0.684 628 0.233 0.0095 Run TR092RN105 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 46 0 143 0.683 719 0.311 0.0111 Set cyclic for zero flapping; nominal fwd flight ref point REC 47 0 143 0.683 1325 0.312 0.0205 REC 48 0 143 0.683 2027 0.311 0.0313 REC 49 0 143 0.683 2615 0.312 0.0404 REC 50 0 144 0.684 3312 0.312 0.0510 REC 51 0 144 0.684 3700 0.313 0.0570 Max CTOS, Torque limited REC 52 0 143 0.684 724 0.311 0.0112 REC 53 0 62 0.684 686 0.134 0.0103 nominal fwd - flight ref. point REC 54 0 15 0.684 3637 0.033 0.0544 hover ref. point REC 55 0 7 201 338 0.044 0.0411 REC 56 0 SIM static REC 57 0 SIM static ZER 58 0 SIM CAL 59 0 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN106 11/9/2018 Helicopter forward flight, thrust sweeps, 90 deg yaw, 57 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 0 200 442 0.000 0.0515 Rotating ref. point REC 10 90 0 0.684 761 0.000 0.0113 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 0 0.684 694 0.000 0.0103 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 12 90 57 0.684 1270 0.125 0.0190 Min CTOS - trim to zero flapping REC 13 90 57 0.684 1938 0.126 0.0290 REC 14 90 57 0.683 2642 0.126 0.0396 REC 15 90 57 0.684 3245 0.126 0.0486 REC 16 90 57 0.683 3600 0.126 0.0540 REC 17 90 57 0.684 3937 0.126 0.0590 REC 18 90 57 0.684 4227 0.126 0.0633 REC 19 90 57 0.683 4686 0.126 0.0703 REC 20 90 57 0.684 4951 0.126 0.0741 REC 21 90 57 0.684 5314 0.126 0.0796 Max CTOS REC 22 90 57 0.684 4919 0.126 0.0737 REC 23 90 57 0.683 4544 0.126 0.0682 REC 24 90 57 0.684 4239 0.126 0.0634 REC 25 90 57 0.684 3943 0.125 0.0591 REC 26 90 57 0.684 3570 0.125 0.0534 REC 27 90 57 0.684 3272 0.125 0.0490 REC 28 90 57 0.684 2573 0.125 0.0386 REC 29 90 57 0.684 1914 0.125 0.0287 REC 30 90 57 0.684 1213 0.125 0.0182 REC 31 90 0 0.684 625 0.000 0.0093 REC 32 90 0 201 527 0.000 0.0625 REC 33 90 SIM static REC 34 90 SIM static ZER 35 90 SIM CAL 36 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN107 11/9/2018 Acoustic BVI helicopter mode testing, yaw and thrust sweeps, 57 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 0 201 448 0.000 0.0535 Rotating ref. point REC 10 90 0 0.684 705 0.000 0.0105 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 57 0.684 3258 0.126 0.0489 Min CTOS - trim to zero flapping REC 12 80 58 0.684 3263 0.126 0.0490 REC 13 80 57 0.684 4942 0.125 0.0741 REC 14 82 57 0.684 4985 0.125 0.0748 REC 15 84 57 0.684 4924 0.125 0.0740 REC 16 86 57 0.684 4895 0.125 0.0735 REC 17 88 58 0.684 4926 0.126 0.0740 REC 18 89 58 0.684 4968 0.126 0.0746 REC 19 90 58 0.684 4974 0.125 0.0746 REC 20 91 57 0.684 4907 0.125 0.0737 REC 21 92 57 0.684 4918 0.125 0.0737 REC 22 93 57 0.684 4927 0.125 0.0740 REC 23 94 57 0.684 4889 0.125 0.0734 REC 24 95 58 0.684 4950 0.126 0.0743 REC 25 96 58 0.684 4895 0.126 0.0735 REC 26 97 58 0.684 4951 0.125 0.0742 REC 27 98 57 0.684 4943 0.125 0.0741 REC 28 99 58 0.684 4926 0.126 0.0740 REC 29 100 58 0.684 4930 0.126 0.0740 REC 30 90 58 0.684 1238 0.125 0.0186 REC 31 90 58 0.684 2000 0.125 0.0300 REC 32 90 58 0.684 2594 0.125 0.0389 REC 33 90 58 0.684 3265 0.126 0.0490 REC 34 90 58 0.684 3568 0.126 0.0536 REC 35 90 58 0.684 3824 0.126 0.0574 REC 36 90 58 0.684 4227 0.126 0.0634 REC 37 90 58 0.684 4590 0.126 0.0689 REC 38 90 58 0.684 4959 0.126 0.0745 Max CTOS REC 39 90 58 0.684 1186 0.126 0.0178 REC 40 90 58 0.684 3234 0.126 0.0486 REC 41 90 0 0.684 527 0.000 0.0079 REC 42 90 0 201 522 0.001 0.0630 REC 43 90 SIM static REC 44 90 SIM static ZER 45 90 SIM CAL 46 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN108 11/13/2018 Airplane forward flight, 0 yaw, 569 rpm, 176, 212 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 0 SIM CAL 2 0 SIM ZER 3 0 SIM CAL 4 0 SIM ZER 5 0 SIM CAL 6 0 SIM REC 7 0 SIM REC 8 0 SIM REC 9 0 0 200 425 0.001 0.0484 Rotating ref. point REC 10 0 7 0.684 705 0.016 0.0104 hover ref. point REC 11 0 60 0.684 677 0.133 0.0101 Airplane mode rpm ref. point REC 12 0 176 0.684 696 0.391 0.0108 Set cyclic for zero flapping; nominal fwd flight ref point REC 13 0 176 0.683 986 0.391 0.0153 REC 14 0 176 0.684 1323 0.391 0.0205 REC 15 0 176 0.683 1638 0.390 0.0255 REC 16 0 176 0.684 2091 0.391 0.0325 REC 17 0 176 0.684 2341 0.390 0.0363 REC 18 0 176 0.684 2744 0.391 0.0426 REC 19 0 176 0.683 2896 0.391 0.0450 Max CTOS, Torque limited REC 20 0 176 0.684 757 0.391 0.0117 REC 21 0 212 0.685 780 0.468 0.0123 Set cyclic for zero flapping; nominal fwd flight ref point REC 22 0 212 0.683 1032 0.469 0.0164 REC 23 0 212 0.683 1511 0.469 0.0240 REC 24 0 212 0.683 1807 0.470 0.0287 REC 25 0 213 0.684 2100 0.470 0.0333 REC 26 0 212 0.684 2173 0.469 0.0344 REC 27 0 213 0.683 2438 0.471 0.0388 Max CTOS, Torque limited REC 28 0 212 0.685 798 0.468 0.0126 REC 29 0 61 0.684 695 0.133 0.0103 nominal fwd - flight ref. point REC 30 0 210 0.685 968 0.463 0.0153 Set cyclic for zero flapping; nominal fwd flight ref point REC 31 0 61 0.684 698 0.133 0.0104 nominal fwd flight ref. point REC 32 0 15 0.684 3650 0.034 0.0541 hover ref. point REC 33 0 8 200 349 0.047 0.0410 REC 34 0 SIM static REC 35 0 SIM static ZER 36 0 SIM CAL 37 0 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN109 11/13/2018 Helicopter fwd flight, thrust sweeps, 569 rpm, 80 - 100 deg yaw, 57 knots Air Exchange Open 100%, Louver 7 Closed, 40x Mode Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip ZER 1 90 SIM CAL 2 90 SIM AB ZER 3 90 SIM CAL 4 90 SIM ZER 5 90 SIM CAL 6 90 SIM REC 7 90 SIM REC 8 90 SIM REC 9 90 3 200 464 0.016 0.0546 Rotating ref. point REC 10 90 3 0.684 669 0.007 0.0099 Helicopter mode rpm; min thrust, watch blade loads - recirculation REC 11 90 57 0.684 3296 0.126 0.0490 Min CTOS - trim to zero flapping REC 12 80 57 0.683 1336 0.125 0.0199 REC 13 80 57 0.684 2017 0.126 0.0300 REC 14 80 57 0.684 2579 0.126 0.0384 REC 15 80 57 0.684 3311 0.126 0.0493 REC 16 80 57 0.684 3641 0.125 0.0543 REC 17 80 57 0.684 3916 0.125 0.0584 REC 18 80 57 0.684 4294 0.126 0.0640 REC 19 80 57 0.684 4610 0.126 0.0687 REC 20 80 57 0.684 4938 0.126 0.0736 REC 21 80 57 0.684 5351 0.126 0.0797 REC 22 80 57 0.684 5615 0.126 0.0837 Max CTOS REC 23 80 57 0.684 1257 0.126 0.0187 REC 24 85 57 0.684 1241 0.126 0.0185 REC 25 85 57 0.684 1937 0.126 0.0288 REC 26 85 57 0.684 2700 0.126 0.0402 REC 27 85 57 0.684 3308 0.126 0.0493 REC 28 85 57 0.684 3645 0.126 0.0543 REC 29 85 57 0.684 3994 0.126 0.0595 REC 30 85 57 0.684 4342 0.126 0.0647 REC 31 85 57 0.684 4654 0.125 0.0694 REC 32 85 57 0.684 4932 0.125 0.0735 REC 33 85 57 0.684 5372 0.125 0.0800 REC 34 85 57 0.684 5640 0.125 0.0839 Max CTOS REC 35 85 57 0.684 1284 0.126 0.0191 REC 36 95 57 0.684 1317 0.125 0.0196 REC 37 95 57 0.684 2008 0.125 0.0299 REC 38 95 57 0.684 2625 0.125 0.0391 REC 39 95 57 0.684 3259 0.125 0.0486 Max CTOS - Inboard spindle loads REC 40 95 57 0.684 1323 0.125 0.0197 REC 41 100 57 0.684 1301 0.126 0.0194 REC 42 100 57 0.684 1909 0.125 0.0284 REC 43 100 57 0.684 2649 0.125 0.0395 REC 44 100 57 0.684 3311 0.125 0.0493 REC 45 100 57 0.684 3641 0.125 0.0543 REC 46 100 57 0.684 3988 0.125 0.0594 REC 47 100 57 0.684 4307 0.125 0.0642 Run TR092RN109 continued Point Data Yaw, VKTS Rotor Thrust, Notes 𝜇 C / 𝜎 T Type Point deg RPM/ lb M tip REC 48 100 57 0.684 4683 0.125 0.0698 REC 49 100 57 0.684 4958 0.125 0.0739 REC 50 100 57 0.684 5348 0.125 0.0797 REC 51 100 57 0.684 5629 0.125 0.0839 Max CTOS REC 52 95 57 0.684 4686 0.126 0.0699 Restarted 95 Deg from higher CTOS REC 53 95 57 0.684 4993 0.126 0.0745 REC 54 95 57 0.684 5253 0.126 0.0784 REC 55 95 57 0.684 5673 0.126 0.0846 Max CTOS REC 56 90 57 0.684 3301 0.125 0.0492 REC 57 90 3 0.684 702 0.006 0.0104 REC 58 90 4 200 530 0.028 0.0627 REC 59 90 SIM static REC 60 90 SIM static ZER 61 90 SIM CAL 62 90 SIM Table 7. TTR/699 Run Log (continued) Run TR092RN110 11/14/2018 Motor checkout (aft motors) & thrust sweeps, 478 & 569 rpm, wind off Air Exchange Open 100%, Louver 7 Open, VS 6 in 80x Mode, VS 4 Closed, VS 3 Open Point Data Yaw, VKTS Rotor Coll., Thrust, Motor Notes C / 𝜎 T Type Point deg RPM deg lb Current ZER 1 0 SIM CAL 2 0 SIM AB ZER 3 0 SIM CAL 4 0 SIM ZER 5 0 SIM CAL 6 0 SIM REC 7 0 SIM REC 8 0 SIM REC 9 0 0 200 5 421 0.0498 REC 10 0 15 565 6 4144 0.0615 200 REC 11 0 21 564 10 6568 0.0978 300 REC 12 0 24 565 13 8273 0.1232 400 REC 13 0 27 564 15 9627 0.1437 500 REC 14 0 27 565 16 10140 0.1510 535 REC 15 0 17 565 6 4114 0.0612 200 REC 16 0 16 565 5 3574 0.0532 REC 17 0 17 564 7 4714 0.0703 REC 18 0 19 564 9 5804 0.0865 REC 19 0 21 565 11 6997 0.1043 REC 20 0 23 564 13 8267 0.1233 REC 21 0 25 565 14 8856 0.1320 REC 22 0 26 565 15 9447 0.1404 REC 23 0 27 565 16 10080 0.1501 REC 24 0 26 564 15 9452 0.1410 REC 25 0 25 564 14 8810 0.1315 REC 26 0 25 565 13 8138 0.1212 REC 27 0 22 565 11 6971 0.1038 REC 28 0 20 565 9 5753 0.0857 REC 29 0 18 564 7 4604 0.0687 REC 30 0 16 565 5 3564 0.0530 REC 31 0 13 481 5 2548 0.0522 REC 32 0 14 481 7 3358 0.0688 REC 33 0 15 481 9 4189 0.0858 REC 34 0 18 481 11 5004 0.1028 REC 35 0 20 481 13 5884 0.1206 REC 36 0 21 481 14 6334 0.1297 REC 37 0 21 481 15 6745 0.1385 REC 38 0 23 481 16 7138 0.1463 REC 39 0 23 481 17 7658 0.1573 REC 40 0 24 481 18 8008 0.1644 REC 41 0 24 481 19 8488 0.1742 REC 42 0 25 481 20 8786 0.1804 REC 43 0 25 481 19 8409 0.1725 REC 44 0 24 481 18 8034 0.1650 REC 45 0 23 481 17 7625 0.1566 REC 46 0 23 481 16 7091 0.1456 REC 47 0 22 481 15 6714 0.1380 REC 48 0 21 481 14 6255 0.1284 REC 49 0 20 481 13 5823 0.1195 Run TR092RN110 Point Data Yaw, VKTS Rotor Coll., Thrust, Motor Notes C / 𝜎 T Type Point deg RPM deg lb Current REC 50 0 18 481 11 4997 0.1025 REC 51 0 17 481 9 4121 0.0846 REC 52 0 16 481 7 3278 0.0672 REC 53 0 13 481 5 2582 0.0530 REC 54 0 7 200 5 343 0.0406 REC 55 0 SIM REC 56 0 SIM static ZER 57 0 SIM CAL 58 0 SIM Table 7. TTR/699 Run Log (concluded) Run TR092RN111 11/06/2018 Yaw sweep, q =75 psf, both aft motors Aerotares: Blades Off, Exposed (Taped) Hub Yoke Bearings Point Data Yaw, Rotor q , Notes Type Point deg RPM psf ZER 1 0 SIM 0 CAL 2 0 SIM 0 AB ZER 3 0 SIM 0 CAL 4 0 SIM 0 REC 5 0 SIM 0 STATIC REC 6 0 129 0 RPM changed during point REC 7 0 100 0 repeat point REC 8 0 201 0 REC 9 0 300 0 REC 10 0 401 0 REC 11 0 478 0 REC 12 0 570 0 REC 13 0 569 75 REC 14 15 570 76 REC 15 30 569 75 REC 16 45 569 76 REC 17 60 570 76 REC 18 63 570 75 REC 19 65 569 75 REC 20 67 569 75 REC 21 69 569 76 REC 22 71 569 75 REC 23 73 569 75 REC 24 75 569 75 REC 25 77 569 75 REC 26 80 570 75 REC 27 0 570 0 REC 28 0 SIM 0 STATIC ZER 29 0 SIM 0 CAL 30 0 SIM 0 AB

Instrumentation and Derived Parameters

Rotor research data are cooperatively processed by NFAC and NASA data systems. The NFAC acquires the data and provides real-time displays of critical operational and Safety of Flight (SOF) data (Reference 14). The NASA Rotor Database Management System (RDMS) performs post-run data processing, including per-revolution windowing and resampling; computes filtered time histories, derived parameters, statistics, and spectra; and stores the data in a network- accessible database.

The NFAC data system includes multiple data streams with different capabilities (Reference 14; see also Reference 1). For each parameter, the effective bandwidth depends on the data system.

Rotor data are typically stored at 256/rev sample rate (BDAS data), whereas most operating conditions and diagnostics data are stored at lower sample rates (SDAS data). Derived parameters may use data from more than one data channel, TTR/699 data parameters are listed in a series of tables below, organized by data type: operating conditions, rotor balance, rotor coefficients, etc. The information is generally the same as is available in the RDMSClient application and Reference 15. The tables given here are intended to simplify searching by collecting nearly all parameter descriptions in one document. Organization of the tables is informed in part by the structure of the RDMS database.

The TTR rotor balance is critical for rotor research. It is described in some detail in a separate section, “Rotor Balance System.” A brief overview of other available data is given immediately below, followed by the data tables.

Table 8, Instrumentation, lists directly measured data; the table notes the data stream used for each item. Table 9 lists Derived Parameters; that is, parameters that depend upon other data or that require special calibration and scaling. Table 10 lists Rotor Coefficients, a special case of Derived Parameters for which all items are non-dimensional. Table 10 also includes non- dimensional velocities. Table 11 lists Wall Pressure measurements. Two tables, Run Parameters (Table 12) and Point Parameters (Table 13), list data status parameters, such as date and time or the number of samples in a data point.

For derived parameters, the traditional NFAC naming convention can be confusing. In particular, “net” may mean either a vector sum of orthogonal loads or the vibratory (peak-to-peak) component with mean values subtracted. In a few cases, both interpretations apply. Derived parameters may also use data from more than one data stream with different sample rates.

Consult Reference 15 for relevant equations.

Microphone data were recorded and stored separately from other TTR data because of the high frequency range required. They are the only parameters that use the DDAS data system. See Reference 7 for details.

Several items appear in more than one table, either to group similar items together, such as tunnel operating conditions, or because a derived parameter is a minor variation on an instrumentation item, such as a change of units.

“Selectable” items are a special case (Table 8). The NFAC data system allows switching between different inputs in case a critical channel should fail mid-run. Manual data entry is also possible. Selectable items are not uniquely associated with any data system.

In order to maintain consistent software, a few items were carried over from earlier tests even when they were not used for TTR or were always zero. In particular, PHI and BETA are irrelevant for TTR, and PSI is replaced by TT_YAW_C. Provisions were made for an anemometer (ANAMOM) but it was never installed.

Several parameters are derived specifically for real-time SOF monitoring but are not stored in the RDMS database nor are they listed here. In other documents, primarily Reference 15, they are denoted by "_SOF" appended to the item name (“tagname”).

The reader is cautioned not to over-interpret the organization and labelling of the TTR/699 database. RDMS was originally built for different rotor systems with different test requirements and adapted for TTR/699. An important consideration was to minimize software changes, sometimes at the expense of strict consistency. For example, IROTOR would rationally be a Run Parameter, but is conventionally listed as a Point Parameter.

Table 8. TTR/699 RDMS Instrumentation Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS Rotor Azimuth AZRAMP_B1M Sawtooth waveform synchronized to 1/rev; master volts √ √ DataAlign_B1M Revolution step - counter; master volts √ √ AZRAMP_B1 Sawtooth waveform synchronized to 1/rev; B1 crate volts √ DataAlign_B1 Revolution step - counter; B1 crate volts √ AZRAMP_B2 Sawtooth waveform synchronized to 1/rev; B2 crate volts √ DataAlign_B2 Revolution step - counter; B2 crate volts √ Rotor Blade REDB_STA32BB Red Blade station 32.00 beam bending 1KΩ Bridge in - lb √ √ REDB_STA32CB Red Blade station 32.00 chord bending 1KΩ Bridge in - lb √ √ REDB_STA58BB Red Blade station 58.5 beam bending 1KΩ Bridge in - lb √ √ REDB_STA58CB Red Blade station 58.5 chord bending 1KΩ Bridge in - lb √ √ REDB_STA70BB Red Blade station 70.0 beam bending 1KΩ Bridge in - lb √ √ REDB_STA70CB Red Blade station 70.0 chord bending 1KΩ Bridge in - lb √ √ REDB_STA70TO Red Blade station 70.0 torsion 1KΩ Bridge in - lb √ √ REDB_STA90BB Red Blade station 90.0 beam bending 1KΩ Bridge in - lb √ √ REDB_STA90CB Red Blade station 90.0 chord bending 1KΩ Bridge in - lb √ √ REDB_STA117BB Red Blade station 117.0 beam bending 1KΩ Bridge in - lb √ √ REDB_STA117CB Red Blade station 117.0 chord bending 1KΩ Bridge in - lb √ √ REDB_STA117TO Red Blade station 117.0 torsion 1KΩ Bridge in - lb √ √ Hub & Yoke HB_ACCELX X - Axis accelerometer in the instrumentation hat piezoelectric g √ √ HB_ACCELY Y - Axis accelerometer in the instrumentation hat piezoelectric g √ √ HB_ACCELZ Z - Axis accelerometer in the instrumentation hat piezoelectric g √ √ HB_PRESS Pressure transducer in the instrumentation hat 350Ω Bridge psia √ REDINBDSPNDL_BS Red inboard spindle beam shear 500Ω Bridge lb √ √ REDINBDSPNDL_CS Red inboard spindle chord shear 500Ω Bridge lb √ √ REDOTBDSPNDL_BS Red outboard spindle beam shear 500Ω Bridge lb √ √ REDOTBDSPNDL_CS Red outboard spindle chord shear 500Ω Bridge lb √ √ REDDL_AX Red drive link axial load 1KΩ Bridge lb √ √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS GRNPTCHLK_AX Green pitch link axial load 1KΩ Bridge lb √ √ REDPTCHLK_AX Red pitch link axial load 1KΩ Bridge lb √ √ WHTPTCHLK_AX White pitch link axial load 1KΩ Bridge lb √ √ REDY_STA12BB_M Red yoke sta 12.75 beam bending 1KΩ Bridge in - lb √ √ REDY_STA12CB_M Red yoke sta 12.75 chord bending 1KΩ Bridge in - lb √ √ REDY_STA12BB Red yoke beam bending, station 12.75, coupled calibration 1KΩ Bridge in - lb √ REDY_STA12CB Red yoke chord bending, station 12.75, coupled calibration 1KΩ Bridge in - lb √ REDY_STA17BB Red yoke sta 17.5 beam bending 1KΩ Bridge in - lb √ √ REDY_STA17CB Red yoke sta 17.5 chord bending 1KΩ Bridge in - lb √ √ Mast Strain MST_STA11PLB Mast bending parallel sta 11.25 (in line with master spline) 1KΩ Bridge in - lb √ √ MST_STA11PRPB Mast bending perp sta 11.25 (90° out from master spline) 1KΩ Bridge in - lb √ √ MST_STA11STRS Mast sta 11.25 stress psi √ √ MST_STA11STRS_V Net vibratory stress mast sta 11.25 psi √ √ MST_STA16PLB Mast bending parallel sta 16.85 (in line with master spline) 1KΩ Bridge in - lb √ √ MST_STA16PRPB Mast bending perp sta 16.85 (90° out from master spline) 1KΩ Bridge in - lb √ √ MST_STA16STRS Mast sta 16.85 stress psi √ √ MST_STA16STRS_V Net vibratory stress mast sta 16.85 psi √ √ MST_STA40PLB Mast bending parallel sta 40.5 (in line with master spline) 1KΩ Bridge in - lb √ √ MST_STA40PRPB Mast bending perp sta 40.5 (90° out from master spline) 1KΩ Bridge in - lb √ √ MST_STA11TO Mast torque sta 11.25 1KΩ Bridge in - lb √ √ MST_STA12TO_B1 Mast torque sta 12.25 A 1KΩ Bridge in - lb √ √ MST_STA12TO_B2 Mast torque sta 12.25 B 1KΩ Bridge in - lb √ √ Hub Temperature HBSPRG_TEMP_WHT Hub spring temp thermocouple (aligned with the white blade) T - type deg F √ √ HBSPRG_TEMP_GRN Hub spring temp thermocouple (aligned with the green blade) T - type deg F √ √ HBSPRG_TEMP_RED Hub spring temp thermocouple (aligned with the red blade) T - type deg F √ √ HBSPRG_TEMP_RD_RTD Hub spring temp RTD (aligned with the red blade) 100Ω platinum deg C √ √ CFBRNG_REDY_RTD CF bearing temp RTD on red yoke 100Ω platinum deg C √ √ CFBRNG_REDY_RTD_180 CF bearing temp RTD on red yoke, 180° from RDT 1 100Ω platinum deg C √ √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS Spinner Support SPUPRSPRT_STA6BB Spinner upper support beam bending at sta 5.97 red spoke 1KΩ Bridge in - lb √ SPUPRSPRT_STA6CB Spinner upper support chord bending at sta 5.97 red spoke 1KΩ Bridge in - lb √ SPUPRSPRT_STA9TO_M Spinner upper support torsion at sta 9.0 red spoke 1KΩ Bridge in - lb √ SPUPRSPRT_STA9TO Spinner upper support torsion at station 9.0, coupled calibration in - lb √ AX_LD_B1 Primary axial load (beam bending green spoke) 1KΩ Bridge lb √ AX_LD_B2 Secondary axial load (beam bending white spoke) 1KΩ Bridge lb √ SPUPRSPRT_WHTTOR Spinner upper support torsion at sta 9.0 white spoke 1KΩ Bridge volts √ SPUPRSPRT_WHTCB Spinner upper support chord bending at sta 5.97 white spoke 1KΩ Bridge volts √ SPUPRSPRT_GRNTOR Spinner upper support torsion at sta 9.0 green spoke 1KΩ Bridge volts √ SPUPRSPRT_GRNCB Spinner upper support chord bending at sta 5.97 green spoke 1KΩ Bridge volts √ SPLWRSPRT_STA5BB Spinner lower support beam bending at sta 5 red spoke 1KΩ Bridge in - lb √ SPLWRSPRT_STA5CB Spinner lower support chord bending at sta 5 red spoke 1KΩ Bridge in - lb √ SPLWRSPRT_STA8TO Spinner lower support torsion at sta 8.5 red spoke 1KΩ Bridge in - lb √ Swashplate SWDR_SHEAR Swashplate driver bracket shear 90 azimuth (bending gage) 1KΩ Bridge lb √ √ SWANTDR_SHEAR_M Anti - drive link shear force, measured 1KΩ Bridge lb √ √ SWANTDR_SHEAR Anti - drive link shear force, accounting for bi - directional slopes 1KΩ Bridge lb √ SWTB_LATB Swashplate support tube lateral bending 1KΩ Bridge in - lb √ √ SWTB_FAB Swashplate support tube F/A bending 1KΩ Bridge in - lb √ √ CTRL_ACT_A_AX Swashplate actuator rod end A 300Ω Bridge lb √ √ CTRL_ACT_B_AX Swashplate actuator rod end B 300Ω Bridge lb √ √ CTRL_ACT_C_AX Swashplate actuator rod end C 300Ω Bridge lb √ √ SWASHPLATE0AZ_M Thermocouple close to the stationary race at 0° azimuth Type T deg F √ SWASHPLATE180AZ_M Thermocouple close to the stationary race at 180° azimuth Type T deg F √ SWASHPLATE0AZ Swashplate temperature in deg C (LXI T/C scanner) Type T deg C √ √ SWASHPLATE180AZ Swashplate temperature in deg C (LXI T/C scanner) Type T deg C √ √ Support Struts STBD_AF_B1 Starboard strut axial force primary 350Ω Bridge in - lb √ STBD_AF_B2 Starboard strut axial force back - up 350Ω Bridge in - lb √ STBD_SF_B1 Starboard strut side force primary 350Ω Bridge in - lb √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS STBD_SF_B2 Starboard strut side force back - up 350Ω Bridge in - lb √ PORT_AF_B1 Port strut axial force primary 350Ω Bridge in - lb √ PORT_AF_B2 Port strut axial force back - up 350Ω Bridge in - lb √ PORT_SF_B1 Port strut side force primary 350Ω Bridge in - lb √ PORT_SF_B2 Port strut side force back - up 350Ω Bridge in - lb √ NOSE_AF_B1 Nose strut axial force primary 350Ω Bridge in - lb √ NOSE_AF_B2 Nose strut axial force back - up 350Ω Bridge in - lb √ NOSE_SF_B1 Nose strut side force primary 350Ω Bridge in - lb √ NOSE_SF_B2 Nose strut side force back - up 350Ω Bridge in - lb √ Microphones MIC1 Free field microphone #1 pascal √ MIC2 Free field microphone #2 pascal √ MIC3 Surface microphone #1 pascal √ MIC4 Surface microphone #2 pascal √ Control Console ACT_A_D Primary LVDT on actuator A LVDT in √ √ ACT_B_D Primary LVDT on actuator B LVDT in √ √ ACT_C_D Primary LVDT on actuator C LVDT in √ √ RB_PITCH Red blade pitch angle potentiometer, wire to blue console 5K pot. deg √ √ HB_FLAP_RB Hub flap angle, red blade deg √ HB_FLAP_RB_M Hub flapping 1 (180° from red blade, wire to blue console) RVDT deg √ √ NREV Encoder pulse A 4096/rev √ NREV_90 Encoder pulse B (90 degree shift) 4096/rev √ 1REV Encoder index 1/rev 1/rev √ ACT_A_DB Secondary LVDT on actuator A LVDT in √ √ ACT_B_DB Secondary LVDT on actuator B LVDT in √ √ ACT_C_DB Secondary LVDT on actuator C LVDT in √ √ GB_PITCH Green blade pitch angle potentiometer, wire to white console 5K pot. deg √ √ HB_FLAP_GRNB Hub flapping angle, green blade deg √ HB_FLAP_GRNB_M Hub flapping 2, 180° from green blade, wire to white console RVDT deg √ √ RPM Rotor revolutions per minute RPM √ √ √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS Flex - coupling FCTQ_B1 Primary flex - coupling torque readings 350Ω Bridge volts √ √ FCTQ_B2 Back - up flex - coupling torque readings 350Ω Bridge volts √ √ FCTH_B1 Primary flex - coupling residual thrust readings 350Ω Bridge volts √ √ FCTH_B2 Back - up flex - coupling residual thrust readings 350Ω Bridge volts √ √ T_FC_TT1 Flex - coupling temperature torque tube 1 RTD deg F √ T_FC_TT2 Flex - coupling temperature torque tube 2 RTD deg F √ T_FC_DIA1 Flex - coupling temperature diameter 1 RTD deg F √ T_FC_DIA2 Flex - coupling temperature diameter 2 RTD deg F √ Rotor Balance Strain AF000_B1 Primary axial force, 0˚ flexure 5KΩ Bridge volts √ √ AF090_B1 Primary axial force, 90˚ flexure 5KΩ Bridge volts √ √ AF180_B1 Primary axial force, 180˚ flexure 5KΩ Bridge volts √ √ AF270_B1 Primary axial force, 270˚ flexure 5KΩ Bridge volts √ √ SF000_B1 Primary side force, 0˚ flexure 5KΩ Bridge volts √ √ SF090_B1 Primary side force, 90˚ flexure 5KΩ Bridge volts √ √ SF180_B1 Primary side force, 180˚ flexure 5KΩ Bridge volts √ √ SF270_B1 Primary side force, 270˚ flexure 5KΩ Bridge volts √ √ NF000_B1 Primary normal force, 0˚ flexure 5KΩ Bridge volts √ √ NF090_B1 Primary normal force, 90˚ flexure 5KΩ Bridge volts √ √ NF180_B1 Primary normal force, 180˚ flexure 5KΩ Bridge volts √ √ NF270_B1 Primary normal force, 270˚ flexure 5KΩ Bridge volts √ √ AF000_B2 Back - up axial force, 0˚ flexure 5KΩ Bridge volts √ √ AF090_B2 Back - up axial force, 90˚ flexure 5KΩ Bridge volts √ √ AF180_B2 Back - up axial force, 180˚ flexure 5KΩ Bridge volts √ √ AF270_B2 Back - up axial force, 270˚ flexure 5KΩ Bridge volts √ √ SF000_B2 Back - up side force, 0˚ flexure 5KΩ Bridge volts √ √ SF090_B2 Back - up side force, 90˚ flexure 5KΩ Bridge volts √ √ SF180_B2 Back - up side force, 180˚ flexure 5KΩ Bridge volts √ √ SF270_B2 Back - up side force, 270˚ flexure 5KΩ Bridge volts √ √ NF000_B2 Back - up normal force, 0˚ flexure 5KΩ Bridge volts √ √ NF090_B2 Back - up normal force, 90˚ flexure 5KΩ Bridge volts √ √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS NF180_B2 Back - up normal force, 180˚ flexure 5KΩ Bridge volts √ √ NF270_B2 Back - up normal force, 270˚ flexure 5KΩ Bridge volts √ √ Rotor Balance Temperature T_B000_MR Metric ring balance temperature, 0˚ station Type T deg F √ √ T_B000_MP Metric post balance temperature, 0˚ station Type T deg F √ √ T_B000_GP Ground ring balance temperature, 0˚ station Type T deg F √ √ T_B000_GR Ground post balance temperature, 0˚ station Type T deg F √ √ T_B045_MR Metric ring balance temperature, 45˚ station Type T deg F √ √ T_B045_GR Ground ring balance temperature, 45˚ station Type T deg F √ √ T_B090_MR Metric ring balance temperature, 90˚ station Type T deg F √ √ T_B090_MP Metric post balance temperature, 90˚ station Type T deg F √ √ T_B090_GP Ground ring balance temperature, 90˚ station Type T deg F √ √ T_B090_GR Ground post balance temperature, 90˚ station Type T deg F √ √ T_B135_MR Metric ring balance temperature, 135˚ station Type T deg F √ √ T_B135_GR Ground ring balance temperature, 135˚ station Type T deg F √ √ T_B180_MR Metric ring balance temperature, 180˚ station Type T deg F √ √ T_B180_MP Metric post balance temperature, 180˚ station Type T deg F √ √ T_B180_GP Ground ring balance temperature, 180˚ station Type T deg F √ √ T_B180_GR Ground post balance temperature, 180˚ station Type T deg F √ √ T_B225_MR Metric ring balance temperature, 225˚ station Type T deg F √ √ T_B225_GR Ground ring balance temperature, 225˚ station Type T deg F √ √ T_B270_MR Metric ring balance temperature, 270˚ station Type T deg F √ √ T_B270_MP Metric post balance temperature, 270˚ station Type T deg F √ √ T_B270_GP Ground ring balance temperature, 270˚ station Type T deg F √ √ T_B270_GR Ground post balance temperature, 270˚ station Type T deg F √ √ T_B315_MR Metric ring balance temperature, 315˚ station Type T deg F √ √ T_B315_GR Ground ring balance temperature, 315˚ station Type T deg F √ √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS Test Section Conditions ALPHA Shaft tilt in wind tunnel axes (selectable) [= TT_YAW_C−90] deg √ ALPHA_SEL Shaft tilt input flag ALPHA_ANA Shaft pitch angle [unreliable] deg √ ALPHA_INP Shaft pitch angle, manual input deg ANAMOM Tunnel speed (anemometer) [not used] BARO Barometric pressure (selectable) psia √ BARO_SEL Barometric pressure input flag BARO_ANA_B Barometric pressure (analog from Edwards Barocel) psia √ √ BARO_ANA_M Barometric pressure (analog from Mensor 2500) psia √ √ BARO_DIG Barometric pressure (digital from Mensor 14500) psia √ √ BARO_DIG_M25 Barometric pressure (digital from Mensor 2500) psia √ √ BARO_INP Barometric pressure from factor table psia √ BDAS_TIME BDAS sample time [rarely used] msec √ DDAS_TIME DDAS sample time [rarely used] msec √ SDAS_TIME SDAS sample time [rarely used] msec √ BETA Sideslip angle (selectable) [not used] deg BETA_SEL Sideslip angle input flag BETA_ANA Sideslip angle [unreliable] deg √ BETA_INP Sideslip angle, manual input deg DELPTR Total pressure correction psf √ DPRS Differential pressure (static q ) √ DPRS_SEL Differential pressure (static q ) input flag DPRS_ANA_M Differential pressure (static q ) (analog from Mensor 2500) psf √ DPRS_DIG_M Differential pressure (static q ) (digital from Mensor 15000) psf √ √ Table 8. TTR/699 RDMS Instrumentation (continued) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS DPRS_DIG_M25 Differential pressure (static q ) (analog from Mensor 2500) psf √ √ DPRS_INP Differential pressure (static q ) from factor table √ DPT Dew point temperature (selectable) deg F √ DPT_SEL Dew point temperature input flag HUM_DPT_ANA Dew point temperature (analog from Vaisala humidity meter) deg F √ √ HUM_DPT_DIG Dew point temperature (digital from Vaisala humidity meter) deg F √ √ HUM_DPT_INP Dew point temperature, manual input deg F √ DQSP Static plate correction psf √ PA Atmospheric pressure at tunnel centerline psfa √ PHI Roll angle (selectable) [not used] deg PHI_ANA Roll angle (positive starboard down) [unreliable] deg √ PR Tunnel reference ring pressure (selectable) psf √ PR_SEL Tunnel reference ring pressure input flag PR_ANA_B Tunnel reference ring pressure (analog from Edwards Barocel) psf √ √ PR_ANA_M Tunnel reference ring pressure (analog from Mensor 2500) psf √ PR_DIG Tunnel reference ring pressure (digital from Mensor 2500) psf √ √ PR_INP Tunnel reference ring pressure, manual input psf √ PSI Yaw angle (selectable) [use TT_YAW_C] PSI_ANA Yaw angle, positive clockwise looking down [unreliable] deg √ PSREF Tunnel static ring reference pressure (selectable) psf √ PSREF_SEL Tunnel static ring reference pressure input flag PSREF_ANA_B Tunnel static reference pressure (analog from Edwards Barocel) psf √ PSREF_ANA_M Tunnel static reference pressure (analog from Mensor 2500) psf √ PSREF_DIG Tunnel static reference pressure (digital from Mensor 2500) psf √ √ PSREF_INP Tunnel static reference pressure, manual input psf √ PS Static pressure at tunnel centerline psfa √ PT Total pressure at tunnel centerline psfa √ Table 8. TTR/699 RDMS Instrumentation (concluded) Data Acquisition System Tagname Description Type Units SDAS BDAS DDAS Virtual Derived SOFDAS SOFDAS Q Corrected tunnel dynamic pressure psf √ Q_SEL Corrected tunnel dynamic pressure input flag QCLU Uncorrected dynamic pressure at tunnel centerline psf √ QU Uncorrected dynamic pressure at ring locations psf √ QU_SEL Uncorrected dynamic pressure input flag TTF Tunnel total temperature (selectable) deg F √ TTF_SEL Tunnel total temperature input flag TTF_ANA Tunnel total temperature (analog from Fluke Black Stack 1560) deg F √ √ TTF_DIG Tunnel total temperature (digital from Fluke Black Stack 1560) deg F √ √ TTF_ANA_SP Tunnel total temperature from Fluke 1560 (analog, spare) deg F √ TTF_INP Tunnel total temperature, manual input deg F √ TTR Tunnel total temperature (Rankine) deg R √ TT_YAW Yaw angle (selectable) deg √ TT_YAW_SEL Yaw angle input flag TT_YAW_ANA Yaw angle (analog source) [unreliable] deg √ TT_YAW_DIG Yaw angle (digital source) deg √ TT_YAW_INP Yaw angle, manual input deg √ TT_YAW_C Corrected yaw angle, + CW looking down, 0 deg pointing upstream deg √ The support struts have two sets of strain gages, labeled “B1” and “B2”. The gage set used is appended to each strut load parameter.

Table 9. TTR/699 Derived Parameters Tagname Description Units Operating Conditions ALPHA Shaft tilt in wind tunnel axes, positive clockwise looking down deg CALPHA_B3 Corrected angle of attack deg CALPHA_B4 Corrected angle of attack deg CONSTF Normalization factor for force parameters lb CONSTM Normalization factor for moment parameters ft - lb CONSTP Normalization factor for power parameters ft - lb/sec DALPHA_B3 Correction offset for angle of attack deg DALPHA_B4 Correction offset for angle of attack deg DELPTR Total pressure correction psf DQSP Static plate correction lb/ft MAT Rotor advancing tip Mach number N/D MTIP Hover tip Mach number N/D MTUN Tunnel Mach number N/D MU Rotor advance ratio (helicopter mode) N/D MUAT Rotor advancing tip advance ratio N/D MUX Inplane advance ratio (helicopter mode) N/D MUY Lateral advance ratio N/D MUZ Axial advance ratio (airplane mode) N/D OMR Rotor tip speed ft/s PA Atmospheric pressure at tunnel centerline psfa PS Static pressure at tunnel centerline psf PT Total pressure at tunnel centerline psf Q Corrected tunnel dynamic pressure psf QCLU Uncorrected dynamic pressure at tunnel centerline psf QU Uncorrected dynamic pressure at ring locations psf REYN Reynolds number 10 /ft RH Test section relative humidity % RHO Air density slug/ft TSF Tunnel sta tic temperature in deg F deg F TSR Tunnel static temperature in deg R deg R TTR Tunnel total temperature in deg R deg R TT_YAW_C Corrected yaw angle, + CW looking down, 0 deg pointing upstream deg Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units VFPS Tunnel speed ft/sec VISC Tunnel air viscosity slug/ft - sec VKTS Tunnel speed knots VPDB Test section dry bulb vapor pressure psf VPDP Test section dew point vapor pressure psf Rotor & Hub A1 Lateral cyclic pitch angle (positive leading edge down at 0 - deg azimuth) deg A1B Lateral cyclic pitch angle (backup) deg B1 Longitudinal cyclic pitch angle (positive leading edge down at 90 - deg azimuth) deg B1B Longitudinal cyclic pitch angle (backup) deg lb AF_BD_PR Axial force from stationary control loads lb AF_BD_SH_A Weight and aero tare corrected shaft axial force (positive starboard) lb AF_BD_SH_B Weight and aero tare corrected shaft axial force (backup, positive starboard) lb AF_BD_SP Axial force from swashplate weight lb in - lb COLL Collective angle deg COLLB Collective angle (backup) deg HB_FLAP_RB Hub flap angle, red blade deg HB_FLAP_GRNB Hub flapping angle, green blade deg IROTOR Rotor configuration N/D LATGIM_GF Gimbal lateral flap angle, green blade, fixed system deg LATGIM_RF Gimbal lateral flap angle, red blade, fixed system deg LNGGIM_GF Gimbal longitudinal flap angle, green blade, fixed system deg LNGGIM_RF Gimbal longitudinal flap angle, red blade, fixed system deg MM_PRESS_FORCE Mast module axial force from internal pressure, positive in NF direction lb MST_STA11STRS Mast station 11.25 stress psi MST_STA11STRS_V Net vibratory stress mast station 11.25 psi MST_STA16STRS Mast station 16.85 stress psi MST_STA16STRS_V Net vibratory stress mast station 16.85 psi NF_BD_PL Normal force from pitch link loads lb NF_BD_PR Normal force from stationary control loads lb PM_BD_PL Pitching moment from pitch link loads ft - lb PM_BD_PR Pitching moment from stationary control loads ft - lb PM_BD_SH_A Weight and aero tare corrected shaft pitching moment (+ nose right) ft - lb PM_BD_SH_B Weight and aero tare corrected shaft pitching moment (backup, + nose right) ft - lb PM_BD_SP Pitching moment from swashplate weight ft - lb Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units REDY_STA12BB Red yoke beam bending, station 12.75, coupled calibration in - lb REDY_STA12CB Red yoke chord bending, station 12.75, coupled calibration in - lb RM_BD_PL Rolling moment from pitch link loads ft - lb RM_BD_PR Rolling moment from stationary control loads ft - lb RM_BD_SH_A Weight and aero tare corrected shaft rolling moment (+ nose down) ft - lb RM_BD_SH_B Weight and aero tare corrected shaft rolling moment (backup, + nose down) ft - lb RM_BD_SP Rolling moment from swashplate weight ft - lb ROTF1 Rotating force parallel to master spline lb ROTF2 Rotating force perpendicular to master spline lb ROTM1 Rotating moment parallel to master spline ft - lb ROTM1PL Rotating moment 1 from pitch link loads ft - lb ROTM2 Rotating moment perpendicular to master spline ft - lb ROTM2PL Rotating moment 2 from pitch link loads ft - lb SF_BD_PR Side force from stationary control loads lb SF_BD_SH_A Weight and aero tare corrected shaft side force (positive down) lb SF_BD_SH_B Weight and aero tare corrected shaft side force (backup, positive down) lb SF_BD_SP Side force from swashplate weight lb SPCOLL Swashplate collective position in SPCOLL_B Swashplate collective position (backup) in SPLAT Swashplate lateral input in SPLONG Swashplate longitudinal input deg SPA1 Swashplate A1 deg SPB1 Swashplate B1 deg SWANTDR_SHEAR Anti - drive link shear force, accounting for bi - directional slopes lb SWASHPLATE0AZ Swashplate temperature in deg C (LXI T/C scanner) deg C SWASHPLATE180AZ Swashplate temperature in deg C (LXI T/C scanner) deg C SPSHEAR Swashplate net shear load lb SPSHEAR_V Swashplate net vibratory shear load lb SWTB_NETB Swashplate support tube net bending moment in - lb SWTB_NETB_V Swashplate support tube net vibratory bending moment in - lb SWTB_SP Swashplate tube support plate stress psi SWTB_SP_V Swashplate tube support plate net vibratory stress psi SWTB_STRESS Swashplate support tube stress location 1 psi SWTB_STRESS_V Swashplate support tube vibratory stress location 1 psi SWTB_BOLT1 Swashplate tube support plate bolt shear stress psi SWTB_BOLT1_V Swashplate tube support plate bolt net vibratory shear stress psi SWTB_BOLT2 Swashplate tube support plate bolt tensile stress psi SWTB_BOLT2_V Swashplate tube support plate bolt net vibratory tensile stress psi Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units Spinner AFATR Tare with rotating spinner for balance axial force (positive starboard ) lb AF_BA_SP Spinner axial force from strain gages, parallel to master spline lb AX_LD_RB Spinner axial load derived solely from red spoke strain gage lb HUB_ACCEL Hub (instrumentation plate) acceleration g HUB_ACCEL_V Net hub vibratory acceleration g NFATR Tare with rotating spinner for balance normal force (positive forward) lb PMATR Tare with rotating spinner for balance pitching moment (positive nose right) ft - lb RMATR Tare with rotating spinner for balance rolling moment (positive nose down) ft - lb RM_BA_SP1 Spinner rolling moment from strain gages ft - lb RM_BA_SP2 Spinner rolling moment from strain gages ft - lb SFATR Tare with rotating spinner for balance side force (positive down) lb SP_PRESS_FORCE Spinner axial force from internal pressure, positive in balance NF direction lb SPRAX_LD Spinner axial load from strain gages, positive in balance NF direction lb SPRF_PERP Spinner rotating side force from strain gages, perpendicular to master spline lb SPRM_PARA1 Spinner rotating moment from spoke gages, axis parallel to master spline ft - lb SPRM_PARA2 Spinner rotating moment from spoke gages, axis parallel to master spline ft - lb SPRM_PERP Spinner rotating moment from spoke gages, perpendicular to master spline ft - lb SPLWRSPRT_SLG Spinner lower support side load lb SPRF_PERP Spinner rotating side force from strain gages, perpendicular to master spline lb SPRM_PARA1 Spinner rotating moment from spoke gages, axis parallel to master spline ft - lb SPRM_PARA2 Spinner rotating moment from spoke gages, axis parallel to master spline ft - lb SPRM_PERP Spinner rotating moment from spoke gages, perpendicular to master spline ft - lb SPUPRSPRT_STA9TO Spinner upper support torsion, station 9.0, coupled calibration in - lb Aerodynamic tare with rotating spinner for flex-coupling torque TQATR ft-lb (positive CW looking towards balance) Rotor Balance Inputs AF_V_B3 Load readings for axial force in balance axes volt AF_V_B4 Load readings for axial force in balance axes volt FCTH_B1 Primary flex - coupling residual thrust readings volt FCTH_B2 Back - up flex - coupling residual thrust readings volt Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units FCTQ_B1 Primary flex - coupling torque readings volt FCTQ_B2 Back - up flex - coupling torque readings volt FCTH_V_B3 Flex - coupling residual thrust readings in balance axes = FCTH_B1 volt FCTH_V_B4 Flex - coupling residual thrust readings in balance axes = FCTH_B2 volt FCTQ_V_B3 Flex - coupling torque readings in balance axes = FCTQ_B1 volt FCTQ_V_B4 Flex - coupling torque readings in balance axes = FCTQ_B2 volt NF_V_B3 Load readings for normal force in balance axes volt NF_V_B4 Load readings for normal force in balance axes volt PM_V_B3 Load readings for pitching moment in balance axes volt PM_V_B4 Load readings for pitching moment in balance axes volt RM_V_B3 Load readings for rolling moment in balance axes volt RM_V_B4 Load readings for rolling moment in balance axes volt SF_V_B3 Load readings for side force in balance axes volt SF_V_B4 Load readings for side force in balance axes volt YM_V_B3 Load readings for yaw moment in balance axes volt YM_V_B4 Load readings for yaw moment in balance axes volt AFWTNRB_B3 Weight tare with nonrotating blade for balance axial force (+ starboard) = 0 lb AFWTNRB_B4 Weight tare with nonrotating blade for balance axial force (+ starboard) = 0 lb NFWTNRB_B3 Weight tare with nonrotating blade for balance normal force (+ forward) = 0 lb NFWTNRB_B4 Weight tare with nonrotating blade for balance normal force (+ forward) = 0 lb PMWTNRB_B3 Wt. tare with nonrotating blade for balance pitching moment (+ nose right) = 0 ft - lb PMWTNRB_B4 Wt. tare with nonrotating blade for balance pitching moment (+ nose right) = 0 ft - lb RMWTNRB_B3 Weight tare with nonrotating blade for balance rolling moment (+ nose down) ft - lb RMWTNRB_B4 Weight tare with nonrotating blade for balance rolling moment (+ nose down) ft - lb SFWTNRB_B3 Weight tare with nonrotating blade for balance side force (positive down) = 0 lb SFWTNRB_B4 Weight tare with nonrotating blade for balance side force (positive down) = 0 lb TQWTNRB_B3 Wt. tare with nonrotating blade for flex - coupling torque (+ CW looking aft) = 0 ft - lb TQWTNRB_B4 Wt. tare with nonrotating blade for flex - coupling torque (+ CW looking aft) = 0 ft - lb Rotor Balance Outputs AF_BAL_B3 Weight and aero tare corrected axial force (positive starboard) lb AF_BAL_B4 Weight and aero tare corrected axial force (positive starboard) lb AF_BD_B3 Axial force at rotor hub in shaft axis (positive starboard) lb AF_BD_B4 Axial force at rotor hub in shaft axis (positive starboard) lb AF_CB_B3 Bias/dbias corrected axial force (positive starboard) = AF_CI_B3 lb Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units AF_CB_B4 Bias/dbias corrected axial force (positive starboard) = AF_CI_B4 lb AF_CI_B3 Interaction corrected axial force (positive starboard) = AF_EU_B3 lb AF_CI_B4 Interaction corrected axial force (positive starboard) = AF_EU_B4 lb AF_CWT_B3 Weight tare corrected axial force (positive starboard) lb AF_CWT_B4 Weight tare corrected axial force (positive starboard) AF_EU_B3 Uncorrected axial force (positive starboard) lb AF_EU_B4 Uncorrected axial force (positive starboard) lb AF_UNC_B3 Combined axial force (positive starboard) = AF_UNC_B3 lb AF_UNC_B4 Combined axial force (positive starboard) = AF_UNC_B4 lb ATANXOL_B3 Angle of resultant rotor force deg ATANXOL_B3_ME – r ecomputed using only the mean values of the individual inputs deg ATANXOL_B4 Angle of resultant rotor force deg ATANXOL_B4_ME – r ecomputed using only the mean values of the individual inputs deg DEQ_B3 Equivalent drag lb DEQ_B3_ME – r ecomputed using only the mean values of the individual inputs lb DEQ_B4 Equivalent drag lb DEQ_B4_ME – r ecomputed using only the mean values of the individual inputs lb DRAG_W_B3 Drag force at rotor hub in wind axis (positive downstream) lb DRAG_W_B4 Drag force at rotor hub in wind axis (positive downstream) lb DRAG_WE_B3 Wall - effect corrected drag force at rotor hub in wind axis (+ downstream) lb DRAG_WE_B4 Wall - effect corrected drag force at rotor hub in wind axis (+ downstream) lb FCTH_CB_B3 Bias/dbias corrected flex - coupling thrust (positive forward) = FCTH_CI_B3 lb FCTH_CB_B4 Bias/dbias corrected flex - coupling thrust (positive forward) = FCTH_CI_B4 lb FCTH_CI_B3 Interaction corrected flex - coupling thrust (positive forward) = FCTH_EU_B3 lb FCTH_CI_B4 Interaction corrected flex - coupling thrust (positive forward) = FCTH_EU_B4 lb FCTH_EU_B3 Uncorrected flex - coupling thrust (positive forward) lb FCTH_EU_B4 Uncorrected flex - coupling thrust (positive forward) lb FCTQ_CB_B3 Bias/dbias corrected flex - coupling torque = FCTQ_CI_B3 ft - lb FCTQ_CB_B4 Bias/dbias corrected flex - coupling torque = FCTQ_CI_B4 ft - lb FCTQ_CI_B3 Interaction corrected flex - coupling torque = FCTQ_EU_B3 ft - lb FCTQ_CI_B4 Interaction corrected flex - coupling torque = FCTQ_EU_B4 ft - lb FCTQ_EU_B3 Uncorrected flex - coupling torque (+ CW looking aft) ft - lb FCTQ_EU_B4 Uncorrected flex - coupling torque (+ CW looking aft) ft - lb FE_B3 Rotor equivalent drag area ft FE_B3_ME – r ecomputed using only the mean values of the individual inputs ft FE_B4 Rotor equivalent drag area ft FE_B4_ME – r ecomputed using only the mean values of the individual inputs ft HFORCE_B3 Corrected rotor balance H - force (positive starboard ) = AF_BD_B3 lb HFORCE_B4 Corrected rotor balance H - force (positive starboard) = AF_BD_B4 lb Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units HP_B3 Horsepower from rotor balance hp HP_B4 Horsepower from rotor balance hp LIFT_W_B3 Lift force at rotor hub in wind axis (positive to right) lb LIFT_W_B4 Lift force at rotor hub in wind axis (positive to right) lb LIFT_WE_B3 Wall - effect corrected lift force at rotor hub in wind axis (positive to right) lb LIFT_WE_B4 Wall - effect corrected lift force at rotor hub in wind axis (positive to right) lb NF_BAL_B3 Weight and aero tare corrected normal force (positive forward) lb NF_BAL_B4 Weight and aero tare corrected normal force (positive forward) lb NF_BD_B3 Normal force at rotor hub in shaft axis (positive forward) lb NF_BD_B4 Normal force at rotor hub in shaft axis (positive forward) lb NF_CB_B3 Bias/dbias corrected normal force (positive forward) = NF_CB_B3 lb NF_CB_B4 Bias/dbias corrected normal force (positive forward) = NF_CB_B4 lb NF_CI_B3 Interaction corrected normal force (positive forward) = NF_EU_B3 lb NF_CI_B4 Interaction corrected normal force (positive forward) = NF_EU_B4 lb NF_CWT_B3 Weight tare corrected normal force (positive forward) lb NF_CWT_B4 Weight tare corrected normal force (positive forward) lb NF_EU_B3 Uncorrected normal force (positive forward) lb NF_EU_B4 Uncorrected normal force (positive forward) lb NF_UNC_B3 Combined normal force (positive forward) lb NF_UNC_B4 Combined normal force (positive forward) lb PITCH_W_B3 Pitch moment at rotor hub in wind axis (positive CW looking down) ft - lb PITCH_W_B4 Pitch moment at rotor hub in wind axis (positive CW looking down) ft - lb PITCH_WE_B3 Wall - effect corrected pitch moment at rotor hub in wind axis (+ nose right) ft - lb PITCH_WE_B4 Wall - effect corrected pitch moment at rotor hub in wind axis (+ nose right) ft - lb PM_BAL_B3 Weight and aero tare corrected pitching moment (positive nose right) ft - lb PM_BAL_B4 Weight and aero tare corrected pitching moment (positive nose right) ft - lb PM_BD_B3 Pitching moment at rotor hub in shaft axis (positive nose right) ft - lb PM_BD_B4 Pitching moment at rotor hub in shaft axis (positive nose right) ft - lb PM_CB_B3 Bias/dbias corrected pitching moment (positive nose right) = PM_CI_B3 ft - lb PM_CB_B4 Bias/dbias corrected pitching moment (positive nose right) = PM_CI_B4 ft - lb PM_CI_B3 Interaction corrected pitching moment (positive nose right) = PM_EU_B3 ft - lb PM_CI_B4 Interaction corrected pitching moment (positive nose right) = PM_EU_B4 ft - lb PM_CWT_B3 Weight tare corrected pitching moment (positive nose right) ft - lb PM_CWT_B4 Weight tare corrected pitching moment (positive nose right) ft - lb PM_EU_B3 Uncorrected pitching moment (positive nose right) ft - lb PM_EU_B4 Uncorrected pitching moment (positive nose right) ft - lb PM_UNC_B3 Combined pitching moment (positive nose right) = PM_CB_B3 ft - lb PM_UNC_B4 Combined pitching moment (positive nose right) = PM_CB_B4 ft - lb ROLL_W_B3 Roll moment at rotor hub in wind axis (positive starboard down) ft - lb ROLL_W_B4 Roll moment at rotor hub in wind axis (positive starboard down) ft - lb Table 9. TTR/699 Derived Parameters (continued) Tagname Description Units ROLL_WE_B3 Wall - effect corrected roll moment at rotor hub in wind axis (+ starboard down) ft - lb ROLL_WE_B4 Wall - effect corrected roll moment at rotor hub in wind axis (+ starboard down) ft - lb RM_BAL_B3 Weight and aero tare corrected rolling moment (positive starboard down) ft - lb RM_BAL_B4 Weight and aero tare corrected rolling moment (positive starboard down) ft - lb RM_BD_B3 Rolling moment at rotor hub in shaft axis (positive nose down) ft - lb RM_BD_B4 Rolling moment at rotor hub in shaft axis (positive nose down) RM_CB_B3 Bias/dbias corrected rolling moment (positive nose down) = RM_CI_B3 ft - lb RM_CB_B4 Bias/dbias corrected rolling moment (positive nose down) = RM_CI_B4 ft - lb RM_CI_B3 Interaction corrected rolling moment (positive nose down) = RM_EU_B3 ft - lb RM_CI_B4 Interaction corrected rolling moment (positive nose down) = RM_EU_B4 ft - lb RM_CWT_B3 Weight tare corrected rolling moment (positive nose down) ft - lb RM_CWT_B4 Weight tare corrected rolling moment (positive nose down) RM_EU_B3 Uncorrected rolling moment (positive nose down) ft - lb RM_EU_B4 Uncorrected rolling moment (positive nose down) RM_UNC_B3 Combined rolling moment (positive nose down) = RM_CB_B3 ft - lb RM_UNC_B4 Combined rolling moment (positive nose down) = RM_CB_B4 ft - lb SIDE_W_B3 Side force at rotor hub in wind axis (positive down) lb SIDE_W_B4 Side force at rotor hub in wind axis (positive down) lb SIDE_WE_B3 Wall - effect corrected side force at rotor hub in wind axis (positive down) lb SIDE_WE_B4 Wall - effect corrected side force at rotor hub in wind axis (positive down) lb SF_BAL_B3 Weight and aero tare corrected side force (positive down) lb SF_BAL_B4 Weight and aero tare corrected side force (positive down) lb SF_BD_B3 Side force at rotor hub in shaft axis (positive down) lb SF_BD_B4 Side force at rotor hub in shaft axis (positive down) lb SF_CB_B3 Bias/dbias corrected side force (positive down) = SF_CI_B3 lb SF_CB_B4 Bias/dbias corrected side force (positive down) = SF_CI_B4 lb SF_CI_B3 Interaction corrected side force (positive down) = SF_EU_B3 lb SF_CI_B4 Bias/dbias corrected side force (positive down) = SF_CI_B4 lb SF_CWT_B3 Weight tare corrected side force (positive down) lb SF_CWT_B4 Weight tare corrected side force (positive down) lb SF_EU_B3 Uncorrected side force (positive down) lb SF_EU_B4 Uncorrected side force (positive down) lb SF_UNC_B3 Combined side force (positive down) lb SF_UNC_B 4 Combined side force (positive down) lb THRUST_B3 Corrected rotor balance thrust in shaft axis (positive forward) = NF_BD_B3 lb THRUST_B4 Corrected rotor balance thrust in shaft axis (positive forward) = NF_BD_B4 lb TORQ_B3 Torque from rotor balance (positive CW looking aft) = YM_BD_B3 ft - lb TORQ_B4 Torque from rotor balance (positive CW looking aft) = YM_BD_B4 ft - lb XFORCE_B3 Corrected rotor balance X - force (positive downstream) = −DRAG_WE_B3 lb XFORCE_B4 Corrected rotor balance X - force (positive downstream) = −DRAG_WE_B4 lb YAW_W_B3 Yaw moment at rotor hub in wind axis (positive nose down) ft - lb YAW_W_B4 Yaw moment at rotor hub in wind axis (positive nose down) ft - lb Table 9. TTR/699 Derived Parameters (concluded) Tagname Description Units YAW_WE_B3 Wall - effect corrected torque moment at rotor hub in wind axis (+ nose down) ft - lb YAW_WE_B4 Wall - effect corrected torque moment at rotor hub in wind axis (+ nose down) ft - lb YFORCE_B3 Rotor balance Y - force (positive down) = SF_BD_B3 lb YFORCE_B4 Rotor balance Y - force (positive down) = SF_BD_B4 lb YM_BAL_B3 Weight and aero tare corrected flex - coupling torque (positive CW looking aft) ft - lb YM_BAL_B4 Weight and aero tare corrected flex - coupling torque (positive CW looking aft) ft - lb YM_BD_B3 Yawing moment at rotor hub in shaft axis positive CW looking aft) ft - lb YM_BD_B4 Yawing moment at rotor hub in shaft axis positive CW looking aft) ft - lb YM_CB_B3 Bias/dbias corrected yaw moment = YM_CI_B3 ft - lb YM_CB_B4 Bias/dbias corrected yaw moment = YM_CI_B4 ft - lb YM_CI_B3 Interaction corrected yaw moment = YM_EU_B3 ft - lb YM_CI_B4 Interaction corrected yaw moment = YM_EU_B4 ft - lb YM_CWT_B3 Weight tare corrected flex - coupling torque (positive CW looking aft) ft - lb YM_CWT_B4 Weight tare corrected flex - coupling torque (positive CW looking aft) ft - lb YM_EU_B3 Uncorrected yaw moment (positive CW looking aft) ft - lb YM_EU_B4 Uncorrected yaw moment (positive CW looking aft) ft - lb YM_UNC_B3 Combined flex - coupling torque (positive CW looking aft) ft - lb YM_UNC_B4 Combined flex - coupling torque (positive CW looking aft) ft - lb Miscellaneous NOSE_AF_B1_C Nose strut axial force primary, corrected for installation lb NOSE_AF_B2_C Nose strut axial force backup, corrected for installation lb NOSE_SF_B1_C Nose strut side force primary, corrected for installation lb NOSE_SF_B2_C Nose strut side force backup, corrected for installation lb PORT_AF_B2_C Port strut axial force backup, corrected for installation lb PORT_SF_B1_C Port strut side force primary, corrected for installation lb PORT_SF_B2_C Port strut side force backup, corrected for installation lb PORT_AF_B1_C Port strut axial force primary, corrected for installation lb STBD_AF_B2_C Starboard strut axial force backup, corrected for installation lb STBD_SF_B1_C Starboard strut side force primary, corrected for installation lb STBD_SF_B2_C Starboard strut side force backup, corrected for installation lb STBD_AF_B1_C Starboard strut axial force primary, corrected for installation lb STRUT_AF_B1 Total strut axial force (primary) lb STRUT_AF_B2 Total strut axial force (backup) lb STRUT_NF_B1 Total strut normal force (primary) lb STRUT_NF_B2 Total strut normal force (backup) lb STRUT_PM_B1 Total strut pitching moment (primary) ft - lb STRUT_PM_B2 Total strut pitching moment (backup) ft - lb STRUT_RM_B1 Strut yawing moment (primary) ft - lb STRUT_RM_B2 Strut yawing moment (backup) ft - lb STRUT_YM_B1 Strut rolling moment (primary) ft - lb STRUT_YM_B2 Strut rolling moment (backup) ft-lb Table 10. TTR/699 Rotor Coefficients Tagname Description CAR_BD_B3 Rotor drag force coefficient in body axis CAR_BD_B4 Rotor drag force coefficient in body axis CAROS_BD_B3 Rotor drag force coefficient over solidity in body axis CAROS_BD_B4 Rotor drag force coefficient over solidity in body axis CDR_W_B3 Rotor drag force coefficient in wind axis CDR_W_B4 Rotor drag force coefficient in wind axis CDR_WE_B3 Rotor drag force coefficient in corrected wind axis CDR_WE_B4 Rotor drag force coefficient in corrected wind axis CDROS_W_B3 Rotor drag force coefficient over solidity in wind axis CDROS_W_B4 Rotor drag force coefficient over solidity in wind axis CDROS_WE_B3 Rotor drag force coefficient over solidity in corrected wind axis CDROS_WE_B4 Rotor drag force coefficient over solidity in corrected wind axis CH_B3 Rotor balance H - force coefficient CH_B4 Rotor balance H - force coefficient CHOS_B3 Rotor balance H - force coefficient over solidity CHOS_B4 Rotor balance H - force coefficient over solidity CLR_W_B3 Rotor lift force coefficient in wind axis CLR_W_B4 Rotor lift force coefficient in wind axis CLR_WE_B3 Rotor lift force coefficient in corrected wind axis CLR_WE_B4 Rotor lift force coefficient in corrected wind axis CLROS_W_B3 Rotor lift force coefficient over solidity in wind axis CLROS_W_B4 Rotor lift force coefficient over solidity in wind axis CLROS_WE_B3 Rotor lift force coefficient over solidity in corrected wind axis CLROS_WE_B4 Rotor lift force coefficient over solidity in corrected wind axis CMXR_BD_B3 Rotor rolling moment coefficient in body axis CMXR_BD_B4 Rotor rolling moment coefficient in body axis CMXR_W_B3 Rotor rolling moment coefficient in wind axis CMXR_W_B4 Rotor rolling moment coefficient in wind axis CMXR_WE_B3 Rotor rolling moment coefficient in corrected wind axis CMXR_WE_B4 Rotor rolling moment coefficient in corrected wind axis CMXROS_BD_B3 Rotor rolling moment coefficient over solidity in body axis CMXROS_BD_B4 Rotor rolling moment coefficient over solidity in body axis CMXROS_W_B3 Rotor rolling moment coefficient over solidity in wind axis CMXROS_W_B4 Rotor rolling moment coefficient over solidity in wind axis CMXROS_WE_B3 Rotor rolling moment coefficient over solidity in corrected wind axis CMXROS_WE_B4 Rotor rolling moment coefficient over solidity in corrected wind axis CMYR_BD_B3 Rotor pitching moment coefficient in body axis CMYR_BD_B4 Rotor pitching moment coefficient in body axis CMYR_W_B3 Rotor pitching moment coefficient in wind axis CMYR_W_B4 Rotor pitching moment coefficient in wind axis CMYR_WE_B3 Rotor pitching moment coefficient in corrected wind axis CMYR_WE_B4 Rotor pitching moment coefficient in corrected wind axis CMYROS_BD_B3 Rotor pitching moment coefficient over solidity in body axis CMYROS_BD_B4 Rotor pitching moment coefficient over solidity in body axis CMYROS_W_B3 Rotor pitching moment coefficient over solidity in wind axis CMYROS_W_B4 Rotor pitching moment coefficient over solidity in wind axis CMYROS_WE_B3 Rotor pitching moment coefficient over solidity in corrected wind axis CMYROS_WE_B4 Rotor pitching moment coefficient over solidity in corrected wind axis Table 10. TTR/699 Rotor Coefficients (continued) Tagname Description CMZR_BD_B3 Rotor yawing moment coefficient in body axis CMZR_BD_B4 Rotor yawing moment coefficient in body axis CMZR_W_B3 Rotor yawing moment coefficient in wind axis CMZR_W_B4 Rotor yawing moment coefficient in wind axis CMZR_WE_B3 Rotor yawing moment coefficient in corrected wind axis CMZR_WE_B4 Rotor yawing moment coefficient in corrected wind axis CMZROS_BD_B3 Rotor yawing moment coefficient over solidity in body axis CMZROS_BD_B4 Rotor yawing moment coefficient over solidity in body axis CMZROS_W_B3 Rotor yawing moment coefficient over solidity in wind axis CMZROS_W_B4 Rotor yawing moment coefficient over solidity in wind axis CMZROS_WE_B3 Rotor yawing moment coefficient over solidity in corrected wind axis CMZROS_WE_B4 Rotor yawing moment coefficient over solidity in corrected wind axis CNR_BD_B3 Rotor lift force coefficient in body axis CNR_BD_B4 Rotor lift force coefficient in body axis CNROS_BD_B3 Rotor lift force coefficient over solidity in body axis CNROS_BD_B4 Rotor lift force coefficient over solidity in body axis CP_B3 Rotor power coefficient from rotor balance CP_B4 Rotor power coefficient from rotor balance CPOS_B3 Rotor power (torque) coefficient over solidity from rotor balance CPOS_B4 Rotor power (torque) coefficient over solidity from rotor balance CPOS_ID_B3 Ideal power coefficient over solidity CPOSID_B3_ME – r ecomputed using only the mean values of the individual inputs CPOS_ID_B4 Ideal power coefficient over solidity CPOSID_B4_ME – r ecomputed using only the mean values of the individual inputs CPOS_NI_B3 Coefficient of non - ideal power over solidity CPOSNI_B3_ME – r ecomputed using only the mean values of the individual inputs CPOS_NI_B4 Coefficient of non - ideal power over solidity CPOSNI_B4_ME – r ecomputed using only the mean values of the individual inputs CPRAT_B3 Ratio of measured power coefficient to the ideal power coefficient CPRAT_B3_ME – r ecomputed using only the mean values of the individual inputs CPRAT_B4 Ratio of measured power coefficient to the ideal power coefficient CPRAT_B4_ME – r ecomputed using only the mean values of the individual inputs CP_B3 Rotor power coefficient from rotor balance CP_B4 Rotor power coefficient from rotor balance CPOS_B3 Rotor power (torque) coefficient over solidity from rotor balance CPOS_B4 Rotor power (torque) coefficient over solidity from rotor balance CPOS_ID_B3 Ideal power coefficient over solidity CPOSID_B3_ME – r ecomputed using only the mean values of the individual inputs CPOS_ID_B4 Ideal power coefficient over solidity CPOSID_B4_ME – r ecomputed using only the mean values of the individual inputs CPOS_NI_B3 Coefficient of non - ideal power over solidity CPOSNI_B3_ME – r ecomputed using only the mean values of the individual inputs CPOS_NI_B4 Coefficient of non - ideal power over solidity CPOSNI_B4_ME – r ecomputed using only the mean values of the individual inputs CPRAT_B3 Ratio of measured power coefficient to the ideal power coefficient CPRAT_B3_ME – r ecomputed using only the mean values of the individual inputs CPRAT_B4 Ratio of measured power coefficient to the ideal power coefficient CPRAT_B4_ME – r ecomputed using only the mean values of the individual inputs Table 10. TTR/699 Rotor Coefficients (continued) Tagname Description CT_B3 Rotor balance thrust coefficient CT_B4 Rotor balance thrust coefficient CTOS_B3 Rotor balance thrust coefficient over solidity CTOS_B4 Rotor balance thrust coefficient over solidity CX_B3 Rotor balance X - force coefficient CX_B4 Rotor balance X - force coefficient CXOS_B3 Rotor balance X - force coefficient over solidity CXOS_B4 Rotor balance X - force coefficient over solidity CYR_BD_B3 Rotor side force coefficient in body axis CYR_BD_B4 Rotor side force coefficient in body axis CYR_W_B3 Rotor side force coefficient in wind axis CYR_W_B4 Rotor side force coefficient in wind axis CYR_WE_B3 Rotor side force coefficient in corrected wind axis CYR_WE_B4 Rotor side force coefficient in corrected wind axis CYROS_BD_B3 Rotor side force coefficient over solidity in body axis CYROS_BD_B4 Rotor side force coefficient over solidity in body axis CYROS_W_B3 Rotor side force coefficient over solidity in wind axis CYROS_W_B4 Rotor side force coefficient over solidity in wind axis CYROS_WE_B3 Rotor side force coefficient over solidity in corrected wind axis CYROS_WE_B4 Rotor side force coefficient over solidity in corrected wind axis ETAP_B3 Propeller propulsive efficiency ETAP_B3_ME – r ecomputed using only the mean values of the individual inputs ETAP_B4 Propeller propulsive efficiency ETAP_B4_ME – r ecomputed using only the mean values of the individual inputs ETAP_GC_B3 Propulsive efficiency with Glauert correction ETAP_GC_B3_ME – r ecomputed using only the mean values of the individual inputs ETAP_GC_B4 Propulsive efficiency with Glauert correction ETAP_GC_B4_ME – r ecomputed using only the mean values of the individual inputs FMERIT_B3 Hover figure of merit FMERIT_B3_ME – r ecomputed using only the mean values of the individual inputs FMERIT_B4 Hover figure of merit FMERIT_B4_ME – r ecomputed using only the mean values of the individual inputs LOD_B3 Rotor lift - to - drag ratio LOD_B3_ME – r ecomputed using only the mean values of the individual inputs LOD_B4 Rotor lift - to - drag ratio LOD_B4_ME – r ecomputed using only the mean values of the individual inputs MAT Rotor advancing tip Mach number MTIP Hover tip Mach number MTUN Tunnel Mach number MU Rotor advance ratio MUAT Rotor advancing tip advance ratio MUX Inplane advance ratio MUY Lateral advance ratio MUZ Axial advance ratio Table 10. TTR/699 Rotor Coefficients (concluded) Tagname Description MUZ_GC_B3 Axial advance ratio with Glauert correction MUZ_GC_B3_ME – r ecomputed using only the mean values of the individual inputs MUZ_GC_B4 Axial advance ratio with Glauert correction MUZ_GC_B4_ME – r ecomputed using only the mean values of the individual inputs VOVH_B3 Non - dimensional hover induced velocity VOVH_B3_ME – r ecomputed using only the mean values of the individual inputs VOVH_B4 Non - dimensional hover induced velocity VOVH_B4_ME – r ecomputed using only the mean values of the individual inputs VPOV_B3 Glauert propeller correction factor (Vʹ/V) VPOV_B3_ME – r ecomputed using only the mean values of the individual inputs VPOV_B4 Glauert propeller correction factor (Vʹ/V) VPOV_B4_ME –recomputed using only the mean values of the individual inputs Table 11. TTR/699 RDMS 40x80 Wall Pressures Tagname Description Tagname Description WP_A_04 Ring A (downstream), panel 4 WP_K_04 Ring K, panel 4 WP_A_09 Ring A (downstream), panel 9 WP_K_09 Ring K, panel 9 WP_A_12 Ring A (downstream), panel 12 WP_K_12 Ring K, panel 12 WP_A_15 Ring A (downstream), panel 15 WP_K_15 Ring K, panel 15 WP_A_18 Ring A (downstream), panel 18 WP_K_18 Ring K, panel 18 WP_A_25 Ring A (downstream), panel 25 WP_K_23 Ring K, panel 23 WP_A_31 Ring A (downstream), panel 31 WP_K_30 Ring K, panel 30 WP_A_35 Ring A (downstream), panel 35 WP_K_35 Ring K, panel 35 WP_A_38 Ring A (downstream), panel 38 WP_K_38 Ring K, panel 38 WP_A_41 Ring A (downstream), panel 41 WP_K_41 Ring K, panel 41 WP_A_44 Ring A (downstream), panel 44 WP_K_44 Ring K, panel 44 WP_A_48 Ring A (downstream), panel 48 WP_K_49 Ring K, panel 49 WP_COM_01 Ring COM, panel 1 WP_L_04 Ring L, panel 4 WP_COM_02 Ring COM, panel 2 WP_L_09 Ring L, panel 9 WP_COM_03 Ring COM, panel 3 WP_L_12 Ring L, panel 12 WP_COM_04 Ring COM, panel 4 WP_L_15 Ring L, panel 15 WP_COM_05 Ring COM, panel 5 WP_L_18 Ring L, panel 18 WP_COM_06 Ring COM, panel 6 WP_L_23 Ring L, panel 23 WP_COM_07 Ring COM, panel 7 WP_L_30 Ring L, panel 30 WP_COM_08 Ring COM, panel 8 WP_L_35 Ring L, panel 35 WP_COM_09 Ring COM, panel 9 WP_L_38 Ring L, panel 38 WP_COM_10 Ring COM, panel 10 WP_L_41 Ring L, panel 41 WP_COM_11 Ring COM, panel 11 WP_L_44 Ring L, panel 44 WP_COM_12 Ring COM, panel 12 WP_L_49 Ring L, panel 49 WP_COM_13 Ring COM, panel 13 WP_M_04 Ring M, panel 4 WP_COM_14 Ring COM, panel 14 WP_M_09 Ring M, panel 9 WP_C_15 Ring C, panel 15 WP_M_18 Ring M, panel 18 WP_C_18 Ring C, panel 18 WP_M_23 Ring M, panel 23 WP_C_23 Ring C, panel 23 WP_M_30 Ring M, panel 30 WP_C_30 Ring C, panel 30 WP_M_35 Ring M, panel 35 WP_C_35 Ring C, panel 35 WP_M_38 Ring M, panel 38 WP_C_38 Ring C, panel 38 WP_M_41 Ring M, panel 41 WP_C_41 Ring C, panel 41 WP_M_44 Ring M, panel 44 WP_C_44 Ring C, panel 44 WP_M_49 Ring M, panel 49 WP_C_49 Ring C, panel 49 WP_N_05 Ring N, panel 5 WP_D_04 Ring D, panel 4 WP_N_09 Ring N, panel 9 WP_D_09 Ring D, panel 9 WP_N_12 Ring N, panel 12 WP_D_12 Ring D, panel 12 WP_N_15 Ring N, panel 15 WP_D_15 Ring D, panel 15 WP_N_18 Ring N, panel 18 WP_D_18 Ring D, panel 18 WP_N_23 Ring N, panel 23 WP_D_23 Ring D, panel 23 WP_N_30 Ring N, panel 30 WP_D_30 Ring D, panel 30 WP_N_35 Ring N, panel 35 WP_D_35 Ring D, panel 35 WP_N_38 Ring N, panel 38 WP_D_38 Ring D, panel 38 WP_N_41 Ring N, panel 41 WP_D_41 Ring D, panel 41 WP_N_44 Ring N, panel 44 WP_D_44 Ring D, panel 44 WP_N_49 Ring N, panel 49 Table 11. TTR/699 RDMS 40x80 Wall Pressures (continued) Tagname Description Tagname Description WP_E_04 Ring E, panel 4 WP_P_05 Ring P, panel 5 WP_E_09 Ring E, panel 9 WP_P_09 Ring P, panel 9 WP_E_12 Ring E, panel 12 WP_P_12 Ring P, panel 12 WP_E_15 Ring E, panel 15 WP_P_18 Ring P, panel 18 WP_E_18 Ring E, panel 18 WP_P_23 Ring P, panel 23 WP_E_30 Ring E, panel 30 WP_P_30 Ring P, panel 30 WP_E_35 Ring E, panel 35 WP_P_35 Ring P, panel 35 WP_E_38 Ring E, panel 38 WP_P_38 Ring P, panel 38 WP_E_41 Ring E, panel 41 WP_P_41 Ring P, panel 41 WP_E_44 Ring E, panel 44 WP_P_44 Ring P, panel 44 WP_E_49 Ring E, panel 49 WP_P_49 Ring P, panel 49 WP_F_04 Ring F, panel 4 WP_R_04 Ring R, panel 4 WP_F_09 Ring F, panel 9 WP_R_09 Ring R, panel 9 WP_F_12 Ring F, panel 12 WP_R_12 Ring R, panel 12 WP_F_15 Ring F, panel 15 WP_R_15 Ring R, panel 15 WP_F_18 Ring F, panel 18 WP_R_18 Ring R, panel 18 WP_F_23 Ring F, panel 23 WP_R_23 Ring R, panel 23 WP_F_30 Ring F, panel 30 WP_R_35 Ring R, panel 35 WP_F_38 Ring F, panel 38 WP_R_41 Ring R, panel 41 WP_F_41 Ring F, panel 41 WP_R_44 Ring R, panel 44 WP_F_49 Ring F, panel 49 WP_S_30 Ring S, panel 30 WP_G_04 Ring G, panel 4 WP_S_35 Ring S, panel 35 WP_G_09 Ring G, panel 9 WP_S_38 Ring S, panel 38 WP_G_12 Ring G, panel 12 WP_S_41 Ring S, panel 41 WP_G_15 Ring G, panel 15 WP_S_44 Ring S, panel 44 WP_G_18 Ring G, panel 18 WP_S_49 Ring S, panel 49 WP_G_23 Ring G, panel 23 WP_T_04 Ring T, panel 4 WP_G_30 Ring G, panel 30 WP_T_09 Ring T, panel 9 WP_G_35 Ring G, panel 35 WP_T_12 Ring T, panel 12 WP_G_38 Ring G, panel 38 WP_T_15 Ring T, panel 15 WP_G_41 Ring G, panel 41 WP_T_18 Ring T, panel 18 WP_G_44 Ring G, panel 44 WP_T_23 Ring T, panel 23 WP_G_49 Ring G, panel 49 WP_V_04 Ring V, panel 4 WP_H_04 Ring H, panel 4 WP_V_09 Ring V, panel 9 WP_H_09 Ring H, panel 9 WP_V_12 Ring V, panel 12 WP_H_12 Ring H, panel 12 WP_V_18 Ring V, panel 18 WP_H_15 Ring H, panel 15 WP_V_23 Ring V, panel 23 WP_H_18 Ring H, panel 18 WP_V_30 Ring V, panel 30 WP_H_23 Ring H, panel 23 WP_V_35 Ring V, panel 35 WP_H_30 Ring H, panel 30 WP_V_38 Ring V, panel 38 WP_H_35 Ring H, panel 35 WP_V_41 Ring V, panel 41 WP_H_38 Ring H, panel 38 WP_V_44 Ring V, panel 44 WP_H_41 Ring H, panel 41 WP_V_49 Ring V, panel 49 WP_H_44 Ring H, panel 44 WP_X_04 Ring X (upstream), panel 4 WP_H_49 Ring H, panel 49 WP_X_09 Ring X (upstream), panel 9 Table 11. TTR/699 RDMS 40x80 Wall Pressures (concluded) Tagname Description Tagname Description WP_J_04 Ring J, panel 4 WP_X_12 Ring X (upstream), panel 12 WP_J_09 Ring J, panel 9 WP_X_15 Ring X (upstream), panel 15 WP_J_12 Ring J, panel 12 WP_X_18 Ring X (upstream), panel 18 WP_J_15 Ring J, panel 15 WP_X_23 Ring X (upstream), panel 23 WP_J_18 Ring J, panel 18 WP_X_30 Ring X (upstream), panel 30 WP_J_23 Ring J, panel 23 WP_X_35 Ring X (upstream), panel 35 WP_J_30 Ring J, panel 30 WP_X_38 Ring X (upstream), panel 38 WP_J_35 Ring J, panel 35 WP_X_41 Ring X (upstream), panel 41 WP_J_38 Ring J, panel 38 WP_X_44 Ring X (upstream), panel 44 WP_J_41 Ring J, panel 41 WP_X_49 Ring X (upstream), panel 49 WP_J_44 Ring J, panel 44 WP_J_49 Ring J, panel 49 Table 12. TTR/699 Run Parameters See the RDMS glossary for detailed descriptions.

Tagname Description Notes PHASE_NUMBER Integer value indicating the phase number within the scope a lways = 1 CONSTANT_ID I nteger value indicating the set of constants used within the scope of a run always = 1 ZERO_PT Zero p oint number used in the data reduction process CAL_PT Calibration p oint number used in the data reduction process ALPHA_REF Reference angle of attack for weight tares always = 0 PSI_REF Reference yaw angle for weight tares always = 0 ALPHA_SEL Flag indicating if the angle is an input (0) or measured (1) always = 0 PSI_SEL Flag indicating if the angle is an input (0) or measured (1) always = 0 PHI_SEL Flag indicating if the angle is an input (0) or measured (1) always = 0 BARO_SEL Flag indicating if the barometric pressure is an input (0) or measured ( 2, 4 ) TS_ANA_DIG Flag indicating if the test conditions are based on analog (0) or digital (1) inputs always = 1 QU_SEL Flag indicating if uncorrected q is a direct (0) or differential (1) measurement BDAS_CHANS Number of BDAS channels read in from the RxxxBDAS.rcfg file BDAS_SCANS Number of BDAS scans per rev read in from the RxxxBDAS.rcfg file DDAS_CHANS Number of DDAS channels read in from the RxxxDDAS.rcfg file DDAS_SCANS Number of BDAS scans per rev read in from the RxxxDDAS.rcfg file SDAS_CHANS Number of SDAS channels read in from the RxxxSDAS.rcfg file always = 0 SDAS_SCANS Number of SDAS scans per rev read in from the RxxxSDAS.rcfg file always = 0 USER_CHANS Number of USERDAS channels always = 0 USER_SCANS Number of USERDAS scans per rev always = 0 BAL_ATARE Balance aero tare set number always = 0 BAL_WTARE Balance weight tare set number always = 0 LDC_ATARE Load cell aero tare set number always = 0 LDC_WTARE Load cell weight tare set number always = 0 SCL_ATARE Scale aero tare set number always = 0 SCL_WTARE Scale weight tare set number always = 0 DESCRIPTION Brief description of a run, used to identify the type of run BETA_SEL Sideslip angle input flag (not used for TTR) always = 0 TT_YAW_SEL F lag indicating if the turntable yaw angle is an input (2) or measured (0) Q_SEL Corrected tunnel dynamic pressure input flag always = 0 PR_SEL Tunnel reference ring pressure input flag PSREF_SEL Tunnel static ring reference pressure input flag DPRS_SEL Differential pressure (static q ) input flag TTF_SEL Tunnel total temperature input flag DPT_SEL Dew point temperature input flag always = 0 SIGNROT Rotor rotation direction, looking from front, +1 for CCW, − 1 for CW always = 1 SIGNTABLE T - frame orientation, looking from top, +1 for CCW, − 1 for CW Table 13. TTR/699 RDMS Point Parameters See the RDMS glossary for detailed descriptions.

Tagname Description Notes TYPE Integer code indicating the point type 0 - 5 TYPE_DESC Text string describing the point type (see TYPE) QUALITY_FLAG Quality flag : 0 = bad, 1= good Always = 1 QUALITY_DESC Quality flag description (see QUALITY_FLAG) Always = “good” BDAS_REVS Number of BDAS revs read in from the RxxxPxxxBDAS.etim file BDAS_SAMPLES Number of BDAS samples read in from the RxxxPxxxBDAS.etim file BDAS_TIME BDAS sample time (msec) read in from the RxxxPxxxBDAS.etim file DDAS_REVS Number of DDAS revs read in from the RxxxPxxxDDAS.etim file DDAS_SAMPLES Number of DDAS samples read in from the RxxxPxxxDDAS.etim file DDAS_TIME DDAS sample time (msec) read in from the RxxxPxxxDDAS.etim file SDAS_REVS Number of SDAS revs read in from the RxxxPxxxSDAS.etim file SDAS_SAMPLES Number of SDAS samples read in from the RxxxPxxxSDAS.etim file SDAS_TIME SDAS sample time (msec) read in from the RxxxPxxxSDAS.etim file Always = 0 USER_REVS Number of USERDAS revs Always = 0 USER_SAMPLES Number of USERDAS samples Always = 0 USER_TIME USERDAS sample time Always = 0 ALPHA_INP ALPHA (factor table angle of attack) value Always = 0 PSI_INP PSI (factor table yaw angle) value Always = 0 PHI_INP PHI (factor table roll angle) value Always = 0 BARO_INP BARO (factor table barometric pressure) value Always = 0 Q_INP q (factor table dynamic pressure) value Always = 0 MIC_COEF_SET Calibration set used to reduce microphone data 1 - 4 DESCRIPTION Brief description of a point Not used ACQ_DATE_TIME Point acquisition time RED_DATE_TIME Point data reduction time Not used BETA_INP Sideslip angle, manual input Always = 0 TT_YAW_INP Yaw angle, manual input PR_INP Tunnel reference ring pressure, manual input Always = 0 PSREF_INP Tunnel static reference pressure, manual input Always = 0 DPRS_INP Differential pressure (static q ) from factor table Always = 0 TTF_INP Tunnel total temperature, manual input Always = 0 HUM_DPT_INP Dew point temperature, manual input Always = 0 IROTOR Rotor configuration : 0 = rotor off, 1 = rotor on ; constant during a run Table 14 summarizes the blade strain gage locations. The torsion gage at station 70 (REDB_STA70TO) failed during Run 86.

Table 14. Blade Strain Gages Station Beam Chord Torsion 0.21 R x x 0.37 R x x 0.45 R x x x 0.58 R x x 0.75 R x x x

Rotor Balance System

Rotor balance data are critical for research and require the most elaborate processing (Reference 15). Summary descriptions of the axis system, measurement ranges and uncertainties, and naming convention are given here.

Aircraft nacelle tilt is simulated by yawing the TTR in the test section. Zero-deg yaw is airplane mode, with the rotor pointing into the wind, and 90-deg yaw is helicopter mode, with the rotor edgewise to the flow. This arrangement best fits the rig and rotor into the oblong 40x80 test section. TTR uses a traditional NFAC rotor axis system, but turned on its side so that rotation in yaw simulates aircraft nacelle pitch (Figure 6). Figure 6 gives the axis system labels; note that this is not a consistent right-handed axis system: by convention, roll and yaw moments are reversed in polarity (Table 15).

Table 15. Rotor Balance Load Definitions and Polarities Load Label Axis Positive Direction Axial Force AF x right Side Force SF y down Normal Force (thrust) NF z forward Lateral Moment RM x nose down Normal Moment PM y nose right Torque YM z opposite to rotation

Balance Coordinate System

AF

X

Shaft

Rotation

RM

NF

Z

YM

PM

SF

Y

Fig. 6. TTR balance axis system, referenced to the rotor hub. In airplane orientation, the x-axis points starboard. In helicopter orientation, the x-axis points aft.

The TTR rotor balance has two independent sets of strain gages, each with its own set of calibration coefficients. By tradition, a set of strain gages and associated calibration coefficients is called a “balance” (not to be confused with the physical rotor balance; the distinction will be made herein where necessary). The best of several such balances derived for the TTR are the “B3” and “B4” balances. Many derived parameters, notably rotor coefficients, are computed for both balances. The balance used is denoted by “B3” or “B4” appended to each coefficient where relevant.

Warning: the RDMS database contains parameters computed with other balance calibrations, noted by “B1”, “B2”, and “B5” suffixes. These parameters are for diagnostics only and are strongly deprecated for research purposes. The reader is further warned not to confuse these alternative balance parameters with backup parameters, typically strain gages, also labeled “B1” and “B2,” or with strut bending gages.

The rotor balance was calibrated when installed on the TTR. Calibration procedures are described in References 4 and 12; the results are summarized in Table 16. The rotor balance data include time-interpolated corrections for zero offsets. The wind-tunnel scales were always locked, so all rotor loads were measured by the balance.

For reference, Table 16 lists the calibration ranges and uncertainties (±2 𝜎 errors) for both B3 and B4 balance calibrations. The B3 data are recommended for research use.

The TTR rotor balance is overdesigned for the 699 rotor. The rotor has a gimballed hub, so it cannot sustain large moments. The balance was calibrated over different load ranges (Reference 4); Table 16 gives calibration uncertainties referenced to the reduced load ranges appropriate for the 699 rotor.

Table 16. Rotor Balance Calibration Ranges and Uncertainties Hub Load Range B3 B3 B4 B4 2 σ Error 2 σ /Range 2 σ Error 2 σ /Range Normal force, NF 15,148 lb 120 lb 0.80 % 137 lb 0.90 % In-plane horizontal, AF ±8,250 lb 25 lb 0.15 % 24 lb 0.14 % In-plane vertical, SF ±8,250 lb 18 lb 0.11 % 17 lb 0.11 % Hub moment, vertical axis, PM ±7,500 ft-lb 175 ft-lb 1.16 % 179 ft-lb 1.19 % Hub moment, horizontal, RM ±7,500 ft-lb 225 ft-lb 1.50 % 217 ft-lb 1.44 % Torque, YM 22,338 ft-lb 93 ft-lb 0.42 % 93 ft-lb 0.41 %

References

1. Acree, C. W. Jr., “Wind Tunnel Performance Tests of a Full-Scale Proprotor on the Tiltrotor Test Rig”, NASA/TM–20210021871, Dec. 2021.

2. Acree, C. W. Jr., “Tiltrotor Test Rig Aerodynamic Tares”, NASA/TM–20210021870, Dec.

2021.

3. Acree, C. W. Jr., “Vertical Climb Testing of the Model 699 Proprotor on the Tiltrotor Test Rig”, NASA/TM–20210021872, Nov. 2021.

4. Acree C. W., Jr., and Sheikman, A. L., “Development and Initial Testing of the Tiltrotor Test Rig.” American Helicopter Society 74th Annual Forum, Phoenix, AZ, May 14-17, 2018.

5. Acree, C. W., Jr., and Sheikman, A. L., and Norman, T. R., “High-Speed Wind Tunnel Tests of a Full-Scale Proprotor on the Tiltrotor Test Rig.” Vertical Flight Society 75th Annual Forum Proceedings, Philadelphia, PA, May 2019.

6. Acree, C. W., Jr., “Vertical Climb Testing of a Full-Scale Proprotor on the Tiltrotor Test Rig,” Vertical Flight Society Aeromechanics for Advanced Vertical Flight Technical Meeting, San Jose, CA, January 21–23, 2020.

7. Schatzman, N. L. and Malpica, C., “Acoustic Testing of the Tiltrotor Test Rig in the National Full-Scale Aerodynamics Complex 40- by 80-Foot Wind Tunnel,” Vertical Flight Society 75th Annual Forum Proceedings, Philadelphia, PA, May 2019.

8. Kottapalli, S., and Acree, C. W., Jr., “Analytical Performance, Loads, and Aeroelastic Stability of a Full-Scale Isolated Proprotor,” American Helicopter Society Technical Conference on Aeromechanics Design for Transformative Vertical Lift, San Francisco, CA, January 16-19, 2018.

9. Kottapalli, S., Russell, C. R., Acree, C. W., Jr., and Norman, T. R., “Aeroelastic Stability Analysis of a Full-Scale Isolated Proprotor on the Tiltrotor Test Rig,” AIAA Paper no. 2019- 2134, Dynamics Specialists Conference, AIAA SciTech Forum Proceedings, San Diego, CA, January 2019.

10. Kottapalli, S., and Acree, C. W., Jr., “Correlation of Full-Scale Isolated Proprotor Performance and Loads,” Vertical Flight Society 75th Annual Forum Proceedings, Philadelphia, PA, May 2019.

11. Kottapalli, S., “Loads Correlation of a Full-Scale Proprotor on the Tiltrotor Test Rig,” Vertical Flight Society Aeromechanics for Advanced Vertical Flight Technical Meeting, San Jose, CA, January 21-23, 2020.

12. Solis, E., and Meyn, L., “Photogrammetric Deflection Measurements for the Tiltrotor Test Rig (TTR) Multi-Component Rotor Balance Calibration,” American Helicopter Society Technical Meeting on Aeromechanics Design for Vertical Lift Proceedings, San Francisco, CA, January 2016.

13. Russell, C. R., and Acree, C. W., “Modal Test and Analysis of the NASA Tiltrotor Test Rig,” American Helicopter Society Technical Conference on Aeromechanics Design for Transformative Vertical Lift, San Francisco, CA, January 16-19, 2018.

14. van Aken, J. and Yang, L, “Development of a new State-of-the-Art Data Acquisition System for the National Full-Scale Aerodynamics Complex Wind Tunnels,” AIAA-2009-1346, 47th AIAA Aerospace Sciences Meeting Proceedings, Orlando, FL, January 2009.

15. Acree, C. W., Jr., Meyn, L., and Norman, T., “TTR/699 Software Reference,” in preparation.