Ice Accretions and Full-Scale Iced Aerodynamic Performance Data for a Two-Dimensional NACA 23012 Airfoil

NASA/TP—2016-218348

Ice Accretions and Full-Scale Iced Aerodynamic

Performance Data for a Two-Dimensional

NACA 23012 Airfoil

Harold E. Addy, Jr., Andy P. Broeren, and Mark G. Potapczuk Glenn Research Center, Cleveland, Ohio Sam Lee Vantage Partners, Brook Park, Ohio Didier Guffond and Emmanuel Montreuil Office National d’Etudes et Recherches Aérospatiales, Châtillon, France Frederic Moens Office National d’Etudes et Recherches Aérospatiales, Meudon, France

April 2016

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NASA/TP—2016-218348

Ice Accretions and Full-Scale Iced Aerodynamic

Performance Data for a Two-Dimensional

NACA 23012 Airfoil

Harold E. Addy, Jr., Andy P. Broeren, and Mark G. Potapczuk Glenn Research Center, Cleveland, Ohio Sam Lee Vantage Partners, Brook Park, Ohio Didier Guffond and Emmanuel Montreuil Office National d’Etudes et Recherches Aérospatiales, Châtillon, France Frederic Moens Office National d’Etudes et Recherches Aérospatiales, Meudon, France National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135

April 2016

Acknowledgments The authors would like to acknowledge the outstanding technical support provided by Mr. David W. Sheldon, Mr. Robert F. Ide, and the staff at NASA’s Icing Research Tunnel and by M. Jean-Claude Traineau, M. Philippe Desplas, M. Denis CassouDeSalle, and the staff at ONERA’s F1 Pressurized, Subsonic Wind Tunnel during the wind tunnel tests described herein.

Level of Review : This material has been technically reviewed by a committee of peers.

Available from NASA STI Program National Technical Information Service Mail Stop 148 5285 Port Royal Road NASA Langley Research Center Springfield, VA 22161 Hampton, VA 23681-2199 703-605-6000 This report is available in electronic form at http://www.sti.nasa.gov/ and http://ntrs.nasa.gov/

Contents

NASA/TP—2016-218348 iii NASA/TP—2016-218348 iv

Ice Accretions and Full-Scale Iced Aerodynamic Performance

Data for a Two-Dimensional NACA 23012 Airfoil

Harold E. Addy, Jr., Andy P. Broeren, and Mark G. Potapczuk National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 Sam Lee Vantage Partners Brook Park, Ohio 44142 Didier Guffond and Emmanuel Montreuil Office National d’Etudes et Recherches Aérospatiales 92322 Châtillon, France and Frederic Moens Office National d’Etudes et Recherches Aérospatiales 92190 Meudon, France Also included herein are the data recorded during a wind

Summary

tunnel campaign conducted in the F1 Subsonic Pressurized This report documents the data collected during the large Wind Tunnel of ONERA. The F1 tunnel is a pressured, high- wind tunnel campaigns conducted as part of the SUNSET Reynolds-number facility that could accommodate the full- project (StUdies oN Scaling EffecTs due to ice) also known as scale (72-in. (182.9-cm) chord) 2D NACA 23012 model. Molds the Ice-Accretion Aerodynamics Simulation study: a joint effort were made of the ice accreted during selected test runs of the by NASA, the Office National d’Etudes et Recherches full-scale model in the IRT. From these molds, castings were Aérospatiales (ONERA), and the University of Illinois. These made that closely replicated the features of the accreted ice. The data form a benchmark database of full-scale ice accretions and castings were then mounted on the full-scale model in the F1 corresponding ice-contaminated aerodynamic performance tunnel, and aerodynamic performance measurements were data for a two-dimensional (2D) NACA 23012 airfoil. The made using model surface pressure taps, the facility force wider research effort also included an analysis of ice- balance system, and a large wake rake designed specifically for contaminated aerodynamics that categorized ice accretions by these tests. Tests were run over a range of Reynolds and Mach aerodynamic effects and an investigation of subscale, low- numbers. For each run, the model was rotated over a range of Reynolds-number ice-contaminated aerodynamics for the angles-of-attack that included airfoil stall.

NACA 23012 airfoil. The low-Reynolds-number investigation The benchmark data collected during these campaigns were, included an analysis of the geometric fidelity needed to reliably and continue to be, used for various purposes. The full-scale assess aerodynamic effects of airfoil icing using artificial ice data form a unique, ice-accretion and associated aerodynamic shapes. performance dataset that can be used as a reference when Included herein are records of the ice accreted during addressing concerns regarding the use of subscale ice-accretion campaigns in NASA Glenn Research Center’s Icing Research data to assess full-scale icing effects. Further, the data may be Tunnel (IRT). Two different 2D NACA 23012 airfoil models used in the development or enhancement of both ice-accretion were used during these campaigns; an 18-in. (45.7-cm) chord prediction codes and computational fluid dynamic codes when (subscale) model and a 72-in. (182.9-cm) chord (full-scale) applied to study the effects of icing. Finally, as was done in the model. The aircraft icing conditions used during these wider study, the data may be used to help determine the level of campaigns were selected from the Federal Aviation geometric fidelity needed for artificial ice used to assess Administration’s (FAA’s) Code of Federal Regulations (CFR) aerodynamic degradation due to aircraft icing. The structured, Part 25 Appendix C icing envelopes. The records include the multifaceted approach used in this research effort provides a test conditions, photographs of the ice accreted, tracings of the unique perspective on the aerodynamic effects of aircraft icing.

ice, and ice depth measurements. Model coordinates and The data presented in this report are available in electronic pressure tap locations are also presented. form upon formal approval by proper NASA and ONERA NASA/TP—2016-218348 1 authorities. Contact the Icing Branch Chief at the NASA Glenn about the extension of those results to larger scale models at Research Center in Cleveland, Ohio, for further information. higher Reynolds numbers for two primary reasons. First, a Wherever practical, both U.S. customary and SI units are smaller scale model accretes ice differently than does a larger presented in this report. The IRT and the models were designed scale model when exposed to the same icing conditions, even if using U.S. customary units, so that system is shown as primary the two models are geometrically similar. This is primarily in those instances with SI as equivalents. The F1 tunnel was because the two models have different water droplet collection designed using SI units, so that system is shown as primary in efficiencies. The shape, amount, and sometimes even the those instances with the U.S. customary equivalents. character of ice accretion features can be vastly different.

A list of symbols and acronyms used in this report is Second, much of the aerodynamic performance data that are presented in Appendix A to aid the reader. available for these smaller scale models with ice shape contamination have been obtained at low Reynolds numbers.

The extension of those results to higher, more flight-typical

Research Objectives

Reynolds numbers has been questioned. Some higher Reynolds number, ice-contaminated, aerodynamic performance data for This research had several objectives. They included both the smaller scale models are available; however, concerns have establishment of benchmark databases of ice accretions and ice- been raised about the ice shapes not being similar to those that accretion aerodynamic effects as well as the development of would accrete on a larger scale model, thereby possibly yielding knowledge bases about the effects of ice accretions and ice- results that were not representative of larger scale model, high- accretion features on aerodynamics. More specifically, these Reynolds-number scenarios.

research objectives were to Data from larger scale, higher Reynolds number aerodynamic performance tests of icing effects are limited for • Establish a database of ice accretions on a large-scale, several reasons. First, flight testing of aircraft with ice two-dimensional (2D) airfoil contamination, either natural or artificial, is both expensive and • Establish a database of geometrically similar ice hazardous. Second, existing icing tunnels are too small to accretions on a small-scale, 2D airfoil conduct thorough aerodynamic performance evaluations of • Develop a database and knowledge base of the effects of icing effects on larger scale models. Finally, conducting icing- ice accretions on the aerodynamics of a large-scale, 2D effects studies in a large, aerodynamic wind tunnel involves a airfoil multistep process that is time consuming and expensive. In this • Provide guidance on the level of ice-accretion geometry last instance, ice is first accreted on a larger scale model in a fidelity needed for accurate simulation of the large icing tunnel. Molds of these ice accretions are then made aerodynamic effects of aircraft inflight icing which preserve most, if not all, of the intricate features of the The databases themselves constitute an important point of ice. From these molds, castings are made, producing accurate reference for the further development and validation of both representations of the ice. The castings are subsequently computational ice-accretion codes as well as computational mounted on the larger scale model and tested in a large fluid dynamics (CFD) codes that are employed to help aerodynamic tunnel. A great deal of labor is involved in making determine the effects of icing on aerodynamics. The knowledge the molds and then the castings.

base provides a reference of full-scale model ice accretions and This research program was undertaken to address the lack of associated higher Reynolds number effects for icing studies data and first-hand knowledge of the aerodynamic effects of ice performed with small-scale model ice accretions at low accreted on a larger scale model at flight Reynolds numbers as Reynolds numbers. Moreover, the knowledge base provides a well as to gain insight into how to relate smaller scale, low- measure of the degree to which ice accretion features must be Reynolds-number ice-contaminated test results to flight.

accurately simulated in an artificial ice shape to yield truly Larger, full-scale models were specifically designed and representative aerodynamic effects. constructed for ice accretion testing and for the higher Reynolds The primary purpose of this report is to present the complete number aerodynamic performance effects testing. These cases datasets collected from the ice accretion tests and from the formed the reference cases for the study. The addition of the large-scale aerodynamic performance testing. Analysis of the corresponding smaller, subscale model, ice accretion and low- performance data in this research is described in Reference 1. Reynolds-number testing allowed a unique opportunity to examine the applicability of that kind of data to higher Reynolds number results. By combining capabilities and

Motivation

sharing costs, the partner organizations were able to undertake A variety of studies regarding the aerodynamic effects of ice the extensive research involved in this project.

accreted on smaller scale, 2D models at lower Reynolds The ultimate goal of this research is to establish methods to numbers have been conducted. Questions persisted, however, accurately evaluate the aerodynamic effects of icing on an NASA/TP—2016-218348 2 aircraft flying in natural icing conditions using ground-based (6.1 m) long. An air-atomizing water spray system located in testing and computational tools. This is a longer term goal that the settling chamber upstream of the test section generates the will require the assessment and simulation of icing effects on cloud. The cloud can be controlled to produce icing conditions swept wings and on wings of very large scale. This longer range over a range of droplet size and liquid water content ( LWC ) goal is beyond the scope of this current research effort. This values. The droplets produced form a spectrum of sizes that is program, however, was developed with such a long-range goal Gaussian in nature and is described by a median volumetric in mind. diameter ( MVD ) (Ref. 11). The IRT can produce clouds with MVD values ranging from 15 to 235 μ m. The LWC (Ref. 11) of the cloud is dependent upon airspeed, but can generally range

Approach

from about 0.3 to 2.5 g/m .

The IRT produces an icing cloud in the test section that is The data presented in this report are part of the aforemen- tioned wider study that is described in a series of reports (Refs. relatively uniform over an area that is approximately 4 ft 2 to 8). That wider study employed a seven-phase approach to (1.2 m) high and 5 ft (1.5 m) wide for the icing conditions used the research. The phases were in this study (Ref. 12). The cloud is considered uniform if its variations in LWC fall within ±20 percent. The temperature of 1. Classification of ice accretions the air in the test section varies less than 1.8 °F (1.0 ° C) from 2. Subscale ice accretion tests the set point and over the area of the uniform cloud (Ref. 13).

3. Subscale aerodynamic performance tests 4. Full-scale ice accretion tests F1 Pressurized, Subsonic Wind Tunnel (F1) 5. Full-scale aerodynamic performance tests 6. Subscale ice-simulation validation aerodynamic perfor- The ONERA F1 facility at Le Fauga-Mauzac, France, is a mance tests pressurized, closed-loop, subsonic wind tunnel (Refs. 14 and 7. Establishment of a subscale ice-contaminated-airfoil 15). The test section is 4.5 m (14.8 ft) wide by 3.5 m (11.5 ft) aerodynamic simulation method high by 11 m (36.1 ft) long. It can be pressurized to 3.85 bar and produce Mach numbers up to a maximum of 0.36 and The data in this report are results from three of the phases and Reynolds numbers up to a maximum of 8 million based on a constitute the large-wind-tunnel campaigns involved in the characteristic length of one-tenth of the square root of the cross- research. Those three phases were (2) Subscale ice accretion sectional area.

tests, (4) Full-scale ice accretion tests, and (5) Full-scale aerodynamic tests. These data have value beyond the scope of this research program, particularly in the development and

Model Descriptions

validation of both ice-accretion and CFD codes.

The three large-wind-tunnel campaigns consisted of two Three different test articles were used to obtain the data campaigns in the NASA Icing Research Tunnel (IRT) and one contained in this report. All three were 2D NACA 23012 in the Office National d’Etudes et Recherches Aérospatiales models. Two were built to fit in NASA’s IRT; one had an (ONERA) F1 Subsonic Pressurized Wind Tunnel. The IRT 18-in. (45.7 cm) chord and the other had a 72-in. (182.9-cm) campaigns will be described first followed by the F1 campaign.

chord. The third was built to fit in the ONERA’s F1 tunnel. It had a 72-in. (182.9-cm) chord.

Facility Descriptions

IRT Subscale Model Two wind tunnels were used to produce the results presented in this report. They are described is this section. The model used for the subscale ice accretion tests in the NASA IRT was a single-element, 2D NACA 23012 with a chord length of 18 in. (45.7 cm). It was made of solid aluminum and Icing Research Tunnel (IRT) spanned the 6 ft (1.8 m) from floor to ceiling of the IRT. It was The NASA IRT at Glenn Research Center in Cleveland, designed with a removable leading edge in order to facilitate the Ohio, is an atmospheric, closed-loop, refrigerated wind tunnel manufacture of high-fidelity 3D replications of the ice for capable of generating an icing cloud for aircraft icing research subsequent performance testing in a dry, aerodynamic tunnel.

and development (Refs. 9 and 10). Air temperature in the tunnel The removable leading edge was a 2.0-ft- (0.6-m-) long section can be controlled from –40 to 40 ° F (–40 to 4.4 ° C). The tunnel of the leading edge centered at model midspan. Three such is capable of airspeeds up to 350 kn (empty). The test section is removable leading edges were made for the campaign. A of the 6 ft (1.8 m) high by 9 ft (2.7 m) wide by about 20 ft model installed in the IRT is shown in Figure 1(a). A NASA/TP—2016-218348 3 IRT Full-Scale Model The IRT full-scale model was also a 2D, single-element NACA 23012 airfoil with the same nondimensional coordinates as the subscale IRT model. It also spanned the 6.0 ft (1.8 m) from floor to ceiling of the IRT. The chord length of the full- scale model was 6.0 ft (1.8 m), four times the chord length of the subscale model. The full-scale model was also machined from solid aluminum and had a removable leading-edge section centered at midspan for use in manufacturing high-fidelity artificial ice shapes. For reasons that will be discussed in the following section, the full-scale removable leading-edge span was limited to 15 in. (38.1 cm). Three removable leading edges were also made for this model. A photograph of this model installed in the IRT test section is shown in Figure 2(a). A cross- sectional diagram depicting the removable leading edge is shown in Figure 2(b).

This model also had a chordwise row of pressure taps to facilitate aerodynamic alignment. This row of taps was located 20 in. (50.8 cm) above the tunnel floor on the model. Pressure tap coordinates for this model are given in Appendix C. A thermocouple was also affixed to the model at approximately midspan and near the tunnel floor to ensure the model reached and maintained proper temperature for the icing tests.

F1 Full-Scale Model Like the IRT models, the F1 full-scale model was a 2D, single-element NACA 23012 airfoil with the same nondimensional coordinates as given in Appendix B. It was also machined out of solid aluminum. Like the IRT full-scale model, it had a chord length of 6.0 ft (1.8 m). It spanned the 3.5 m (11.5 ft) from floor to ceiling of the F1 tunnel. A photograph of the model installed in the F1 tunnel is shown in Figure 3(a).

The F1 model had two full-span removable leading edges.

Figure 1.—IRT subscale model for ice accretion testing. (a) Photo. (b) Cross section. Dimensions are in inches One was a clean leading edge that was used for measuring the (millimeters).

baseline aerodynamic performance of the model. The other, the ice leading edge, was designed to allow attachment of artificial ice castings made from molds of ice accreted on the full-scale model in the IRT. A cross-sectional sketch of the model and diagram of a cross section of the model with the removable two leading edges, along with a photo of one of the artificial ice leading edge depicted is shown in Figure 1(b). Model castings, is shown in Figure 3(b). Both the clean leading edge coordinates are given in Appendix B.

and the ice leading edge spanned the entire length of the model, The model also had a chordwise row of pressure taps located but were made in two spanwise sections to facilitate changeover 19-7/8 in. (50.5 cm) from the floor along the span of the model.

while the model was installed in the test section in the tunnel.

These pressure taps were used to aerodynamically align the One section was 10.73 ft (3.3 m) long, and the other was 0.73 ft model in the tunnel. Pressure tap coordinates are listed in (0.2 m) long.

Appendix C. A thermocouple was affixed to the model at The F1 model had both chordwise and spanwise rows of midchord near the tunnel floor to ensure it reached and pressure taps. The chordwise row was located 5.0 ft (1.5 m) maintained the proper temperature for a given test run.

above the floor of the F1 test section. The spanwise rows were NASA/TP—2016-218348 4 Figure 2.—IRT full-scale model for ice accretion testing. (a) Photo. (b) Cross section. Dimensions are in inches (millimeters).

NASA/TP—2016-218348 5 Figure 3.—F1 full-scale model for aerodynamic testing. (a) Photo. (b) Cross section. (c) Artificial ice casting.

NASA/TP—2016-218348 6 located at 70 percent chord on the upper surface and toward determination of these categories was part of the initial each end of the model. All pressure tap locations for this model investigation of this program and is described in detail in are given in Appendix C. Reference 2. The test matrices for both the subscale and the full- The artificial ice castings used in the F1 tests were made from scale IRT campaigns are given in Appendix D of this report.

ice accreted on the removable leading-edge section of the full- scale IRT model. The removable leading edge of the IRT full- IRT Test Procedure scale model was limited to 1.25 ft (0.38 m) for two major reasons. First, the weight of a larger removable leading edge The procedure for each test point in the test matrices would have made it very difficult to remove from the model consisted of several steps. The tunnel was cooled and the model without damaging the accreted ice. Second, molds of ice must angle-of-attack ( AoA ) was adjusted to the desired setting. The have some flexibility in order to remove them from the ice tunnel air speed and temperature were set to their desired casting once it has been poured and has set up in the mold. The values, and the model was allowed to come to temperature. The flexibility, though, means that large molds do not support their tunnel’s cloud was turned on, and the model was exposed to own weight well, and the resulting casting is distorted. Multiple icing conditions for the predetermined length of time. Once the castings were, therefore, required to cover the entire 11.46 ft total exposure time was met, the cloud was turned off and the (3.5 m) span of the two-dimensional F1 model. The original tunnel’s airspeed was brought to idle. The test section was then mold made of accreted ice is often damaged when removing it opened, and researchers entered the tunnel to take photographs from the casting. Therefore, a second mold, called a production of the ice accreted on the model. The ice was then cut using a mold, is made from the original casting, typically called the warmed metal plate. This allowed a cardboard template cut to master casting. The production mold is of a more durable the shape of the airfoil leading edge to be inserted into the ice material than the original mold because the master casting is so that its profile could be traced with a pencil. Typically, three more durable than the accreted ice, which would be damaged tracings of the ice were made: one at the model (tunnel) by the production molding process. The multiple castings centerline and one each at the locations of maximum and required for the F1 model were then made from the production minimum ice accretion within the area of uniform icing cloud mold. Eleven such castings were used to cover the span of the in the tunnel. Measurements of the thickness of the ice at each F1 model. Chordwise pressure taps were installed in 1 of these cut were also made. For the runs where a mold was made, only 11 castings for each ice shape at the same spanwise location as two cuts and tracings of the ice were made, one at each end of the row of chordwise pressure taps on the main part of the the removable leading edge so that the combination of ice and model. Coordinates for the locations of the pressure taps in the leading edge could be removed from the model. The omission castings are also given in Appendix C.

of the centerline cut for these runs also left the ice intact for the mold. For the test runs where the desired ice accretion was an

Test Descriptions

initial roughness shape, no tracings were made because the ice was too thin to trace. Tracings were digitized by hand using a Descriptions of the test campaigns conducted in the two wind digitizing tablet after the tests were completed. Photographs, tunnels are described in this section.

digitized tracings, and ice thickness measurements are shown for each test point in Appendixes E and F for the subscale and IRT Tests full-scale IRT tests, respectively.

Two test campaigns were completed in the NASA IRT at Molds were made of select ice accretions throughout each of Glenn Research Center: one with the subscale NACA 23012 the icing test campaigns. The ice accretions were selected to model and one with the full-scale NACA 23012 model. As obtain ice shapes representative of each of the four categories discussed previously, the primary objective of these tests was discussed earlier. Test conditions were sometimes adjusted to obtain ice shapes for investigating aerodynamic performance slightly to obtain the desired ice shapes. Mold materials were effects. Several flight scenarios where a turboprop commuter prepared before the tests each day as described in Reference 16.

aircraft might encounter icing conditions were used as a When a desired ice accretion was selected for the molding baseline for setting icing conditions in the IRT. The icing process, the removable leading edge, with the accreted ice, was conditions were limited to those described in the Federal unbolted and pulled away from the model. It was then mounted Aviation Administration’s (FAA’s) Code of Federal in a box, and mold material was poured in around the ice and Regulations, 14 CFR Part 25 Appendix C, for this program. The leading edge. The assembly was then placed in a cold room goal of the overall study, however, was to obtain ice shapes where the mold material was allowed to cure for 6 to 8 hr. After representative of four different ice shape categories based upon curing, the mold boxes were disassembled so that the molds types of aerodynamic effects: (1) horn ice, (2) streamwise ice, could be removed. The removable leading edges and mold (3) spanwise ridge ice, and (4) initial roughness ice. The boxes were then readied for the next tunnel run.

NASA/TP—2016-218348 7 With the exception of the spanwise ridge ice accretion, the ice model. All pressure tap locations on the model are given in was accreted on both the subscale and full-scale airfoil models Appendix C.

without ice protection to obtain ice representative of three of the The tunnel also had surface pressure taps located on both four different ice shape categories identified in the first phase of walls and the ceiling of the test section (Ref 17). Each of the the research. Spanwise ridge ice is a type of ice that might form two walls had three axially oriented rows of taps: one at 7.7 cm on an aircraft wing in conjunction with the operation of its ice (3.0 in.) above tunnel centerline, one 90.4 cm (35.6 in.) above protection while flying in extreme icing conditions, such as in a centerline, and one 7.5 cm (29.5 in.) below centerline. The cloud of either unusually high LWC or MVD . In these conditions, ceiling also had three rows of taps: one at –75.0 cm (–29.5 in.), ice can form on a wing downstream of the ice-protected leading one at –1.0 cm (–0.39 in.), and one at +73.0 cm (+28.7 in.) with edge; either by warm water flowing back to a cold surface or by respect to model chord. Each axial row had 15 pressure taps a high number of large droplets impinging aft of the protected spaced 50.0 cm (19.7 in.) apart. The rows started at 350 cm area. In these cases, a forward-facing thickness of ice (a ridge) (137.8 in.) upstream of the turntable center and ended the same forms that is some distance aft of the leading edge of the wing distance downstream.

and is oriented along the length (span) of it. The shape and A wake rake was designed and built specifically for the F1 placement of the spanwise ridge ice accretion give it unique tests conducted as part of this program. It spanned 4.36 m (14.3 aerodynamic characteristics. To generate a representative ft) of the 4.5 m (14.8 ft) width of the tunnel and was supported spanwise ridge ice accretion in the IRT, a thin, electric-foil heater at each end by structural supports mounted to the floor. It was was affixed to a removable leading edge of both the subscale and located at a height of 192.5 cm (75.8 in.) from the tunnel floor.

full-scale models to simulate the presence of a thermal ice The rake probe tips were located 1-1/2 chord lengths protection system. Heater installation and operation were downstream of the trailing edge of the model. There were 102 adjusted to obtain the desired spanwise ridge ice shape. Once the total pressure probes spaced 2.0 cm (0.8 in.) apart and 21 static desired spanwise ridge ice accretion had been achieved, both the pressure probes spaced 10.0 cm (3.9 in.) apart. Both sets of icing conditions and the heater operation were repeated for the probes were centered at the horizontal centerline of the tunnel.

mold run. Thermal analysis of heater operation during the Two sets of guy-wires were used to stabilize the rake. The wires generation of these spanwise ridge ice shapes was beyond the were anchored to the ceiling and floor at approximately 112.0 scope of this investigation. cm (44.3 in.) from each end of the rake. A photo of the wake rake is shown in Figure 4.

F1 Tests One aerodynamic performance test campaign was completed in the ONERA F1 facility at Le Fauga-Mauzac, France. A total of six ice shapes were selected from the full-scale ice accretion tests conducted in the IRT for the F1 Pressurized, Subsonic Wind Tunnel (F1) campaign: one horn shape, one spanwise ridge shape, two streamwise shapes, and two initial ice roughnesses. With the clean leading edge and a set of runs with boundary layer trips attached to the clean leading edge, there were a total of eight model configurations tested during the F1 campaign.

Aerodynamic performance measurements were made in the F1 tunnel using a force balance, surface pressure, and wake rake systems. The external force balance was mounted in a turntable in the floor of the F1 tunnel. The model was mounted vertically, in a cantilevered fashion, from the floor turntable. A mechanical stop-pin was used at the ceiling to prevent the model and force balance system from being overloaded.

As noted earlier, the model had two sets of surface pressure taps. One was oriented in the chordwise direction near the center of the model; at 60 in. (152.4 cm) above the tunnel floor.

The other set was oriented in the spanwise direction on the upper surface of the model, at 70 percent of the chord length.

Each artificial ice shape also had a chordwise row of pressure taps in line with the chordwise row on the main body of the Figure 4.—F1 wake rake.

NASA/TP—2016-218348 8 TABLE I.—ABSOLUTE UNCERTAINTIES OF AERODYNAMIC F1 Test Procedure PERFORMANCE PARAMETERS MEASURED DURING ICING STUDIES IN ONERA F1 TUNNEL Each of the eight model configurations described above was Angle of attack (deg) .............................................................. ± 0.02 run over a series of seven Mach and Reynolds number Lift coefficient, balance ....................................................... ± 0.010 combinations. These Mach and Reynolds number combinations Pitching moment coefficient, balance ................................. ± 0.0007 for each model configuration are given in Tables D.3 to D.18 in Pressure coefficient ............................................................... ± 0.015 Appendix D of this report. The Lot number for each test point Lift coefficient, surface pressures ....................................... ± 0.0070 is also shown in the tables. For the F1 tests, the Lot number is Pitching moment coefficient, surface pressures .................. ± 0.0024 used to designate a set of data recorded during the run. Some Drag coefficient, wake rake .............................................. ± 0.00048 variation in the Reynolds and Mach numbers from the intended set point was encountered due to constraints in tunnel operation.

The ranges over which the Reynolds and Mach numbers varied Corrections for each set point is noted in the test matrices found in those Wind tunnel wall corrections were applied to the lift, drag, tables in Appendix D of this report.

pitching moment, and model surface pressure coefficients and At each combination of Reynolds number and Mach number, to the AoA according to the widely accepted methods as the model was rotated through a range of AoA s. Aerodynamic described in Barlow, Rae, and Pope (Ref. 18) and Allen and performance data were recorded over the range of AoA s such Vincenti (Ref. 19). Another correction procedure was that performance curves could be generated. These data were investigated, considering the pressure signature at the tunnel obtained in two different ways: continuous sweep and fixed walls and the wake rake drag data. This procedure was derived pitch. In the continuous-sweep method, the model was from one used at the Nationaal Lucht-en continuously rotated at a rate of 0.1 ° AoA per second from a low Ruimtevaartlaboratorium High Speed Tunnel (NLR–HST), value (0 ° or lower AoA ) through stall or until model loading with some adaptations to the F1 setup. A detailed analysis of reached a limit, whichever occurred first. In fact, the model load this tunnel wall correction procedure was done by Moens limit was only reached for one combination of Reynolds and (Ref. 20). It was found that both procedures led to similar Mach numbers for one configuration: the low-Mach-number, results over a wide part of the AoA range. Some slight high-Reynolds-number setpoint for the clean configuration. For differences were found to exist at the maximum lift coefficient the fixed-pitch method, the model’s AoA was set at several in a region where the theoretical assumptions of both models discrete values where data were collected over several are questionable. The corrected data provided in this report recording scans. The scans of data for each AoA were then correspond to the former procedure, using the following processed and averaged to give performance values at each equations: discrete AoA . For the continuous-pitch runs, there is typically one Lot number for each combination of Mach and Reynolds π c numbers. For the fixed-pitch runs, there is one Lot number for   = σ (1)   each AoA at each combination of Mach and Reynolds numbers. 2 h

( ) M 1 48   −

F1 Measurement Accuracy c 1   = τ   (2) h 4   The uncertainties of the aerodynamic measurements made in the F1 tunnel are listed in Table I (Ref. 17). The values given in the table are absolute uncertainties. At lower values of the − M 2 σ Λ = ε (3) sb 2 / 1 aerodynamic measurements, the uncertainties, in terms of a

( ) − M 1

relative value, become more significant. In a pressure tunnel such as the F1 where the range over which pressures might need where Λ = 0.25 (from Fig. 9.17 in Ref. 18).

to be measured is relatively large, the measurements made at lower pressures have a higher relative uncertainty. At lower 2 2

( )( ) M 4 . 0 1 M 2 + −

Mach numbers, pressure transducers are often measuring in the C τ = ε (4) wake d, wb M 1 − lower part of their range, leading to higher relative uncertainty values. This can be seen in some of the wake rake pressure plots 2 / 1 90 σ at low Mach number.

( ) ( ) 4 M 1 C C + − + α = α (5)

bal m, bal l, bal cor, π NASA/TP—2016-218348 9 C measured surface-pressure coefficient 90 σ p 2 / 1 (6)

( ) ( ) 4 M 1 C C + − + α = α

psi m, psi l, psi cor, π F1 Test Results

( ) 1 ε − ε − σ − = C C (7)

wb sb bal l, cor bal, l, Results from the full-scale tests at the F1 tunnel are shown in Appendix G. The data are grouped by model configuration. For

( ) 1 ε − ε − σ − = C C (8)

wb sb psi l, cor psi, l, each configuration, complete sets of data are shown for each combination of Mach and Reynolds numbers. Lift, drag, and   − M 6 . 0 3 pitching moment coefficients as a function of AoA are shown   ε − ε − = 1 C C (9) wb sb wake d, cor wake, d,   first. Data from both the continuous-sweep and the fixed-pitch − M 2   methods are shown. For the continuous-sweep method, the data are shown in one-half-degree AoA increments. Each of these C bal l,

( ) 1 C C + ε − ε − = (10)

wb sb bal m, cor bal, m, data points is an average of five consecutive scans: the scan at the AoA shown, the two prior, and the two after. The lift and pitching moment performance data shown for the clean model C psi l, (11)

( ) 1 C C + ε − ε − =

and the model with trip strips have been calculated from the wb sb psi m, cor psi, m, model surface pressure measurements. For all of the model configurations with artificial ice shapes, the lift and pitching C p (12) = C cor p, 2 moment performance data shown are from the force balance ( ) 1 ε + ε + wb sb measurements. In general, the performance data agree well where between the force balance and model surface pressure measurements. Ice-contaminated models, however, tend to σ model chord-to-test-section height parameter, with experience a higher level of unsteady flow. Because the force compressibility correction balance measurements could be better filtered for the unsteady M Mach number effects than the pressure tap measurements, the data from the c chord length force balance measurements are shown for the model h test-section height configurations with artificial ice shapes. For reference τ model chord-to-test-section height parameter purposes, data from the clean model continuous pitch test runs ε solid blockage correction factor sb are co-plotted along with the performance for each of the other Λ airfoil geometry parameter model configurations. All drag coefficient data shown are ε wake blockage correction factor wb calculated from the wake rake pressure measurement.

C measured drag coefficient from wake-survey data d,wake The model surface pressure coefficients, wall surface α corrected angle of attack, using force-balance data pressure coefficients, ceiling surface pressure coefficients, and cor,bal for corrections wake rake pressure data presented are from the fixed-pitch data α measured angle of attack collection method only. These data are shown for each AoA at which the fixed-pitch data were recorded. Side wall surface C measured lift coefficient from force-balance data l,bal pressure data are designated either “pressure” or “suction,” C measured quarter-chord pitching moment coefficient m,bal from force-balance data corresponding to the side of the model that wall was facing. For these wall pressure coefficient data, the three wall taps furthest α corrected angle of attack, using force surface- cor,psi downstream of the lower two rows of taps were affected by the pressure data for corrections presence of the wake rake vertical supports. These data were, C measured lift coefficient from surface-pressure data l,psi therefore, not shown in the plots. Similarly for the ceiling C measured quarter-chord pitching moment coefficient m,psi pressure coefficient data, several of the taps in the row closest from surface-pressure data to the model chord were covered by the model itself. These data C corrected lift coefficient from force-balance data l,bal,cor were also not shown in the plots. No corrections have been C corrected lift coefficient from surface-pressure data l,psi,cor applied to either the wall or ceiling surface pressure data.

C corrected drag coefficient from wake-survey data d,wake,cor C corrected quarter-chord pitching moment coefficient m,bal,cor

from force-balance data Concluding Remarks

C corrected quarter-chord pitching moment coefficient m,psi,cor The data presented in this report are from an extensive from surface-pressure data research and testing program to investigate the aerodynamic C corrected surface-pressure coefficient p,cor performance effects of ice accretions on a full-scale model and NASA/TP—2016-218348 10 to establish methods to faithfully simulate those results on a ice-contaminated aerodynamics, and the applicability and subscale model at lower Mach and Reynolds numbers. The limitations of subscale ice-contaminated aerodynamics testing.

database herein forms a benchmark for computational fluid It also provides a means to evaluate the degree of geometric dynamic simulation and ice accretion code development and similarity needed in the ice simulation to obtain representative validation. The knowledge base formed and described in results to an acceptable level of uncertainty.

interim reports of the research provides extensive insight in to the aerodynamic effects of icing, the degree to which ice Glenn Research Center features need to be faithfully simulated for accurate National Aeronautics and Space Administration aerodynamic simulation, Mach and Reynolds number effects in Cleveland, Ohio, April 28, 2016 NASA/TP—2016-218348 11

Appendix A.—Nomenclature

2D two dimensional CFR Code of Federal Regulations 3D three dimensional F1 ONERA Subsonic Pressurized Wind Tunnel AoA angle of attack h test-section height b model span length FAA Federal Aviation Administration c model chord length IRT NASA Icing Research Tunnel C drag coefficient LWC liquid water content d C measured drag coefficient from wake-survey data M Mach number d,wake C corrected drag coefficient from wake-survey data MVD median volumetric diameter d,wake,cor C lift coefficient NLR–HST Nationaal Lucht-en Ruimtevaartlaboratorium l High Speed Tunnel C measured lift coefficient from force-balance data l,bal ONERA Office National d’Etudes et Recherches C corrected lift coefficient from force-balance data l,bal,cor Aérospatiales C measured lift coefficient from surface-pressure l,psi Re Reynolds number data T static temperature s C corrected lift coefficient from surface-pressure l,psi,cor T total temperature t data V air speed C moment coefficient m α measured angle of attack C measured quarter-chord pitching moment m,bal coefficient from force-balance data α corrected angle of attack, using force-balance data cor,bal for corrections C corrected quarter-chord pitching moment m,bal,cor coefficient from force-balance data α corrected angle of attack, using force surface- cor,psi pressure data for corrections C measured quarter-chord pitching moment m,psi ε solid blockage correction factor coefficient from surface-pressure data sb ε wake blockage correction factor C corrected quarter-chord pitching moment wb m,psi,cor coefficient from surface-pressure data Λ airfoil geometry parameter C measured surface-pressure coefficient p σ model chord-to-test-section height parameter, with compressibility correction C corrected surface-pressure coefficient p,cor τ model chord-to-test-section height parameter CFD computational fluid dynamics NASA/TP—2016-218348 13

Appendix B.—NACA 23012 Model Coordinates

TABLE B.1.—NACA 23012 AIRFOIL COORDINATES x / c y / c x / c y / c x / c y / c x / c y / c 1.00000 0.00126 0.29422 0.07561 0.00219 –0.00444 0.31988 –0.04491 0.98045 0.00441 0.28047 0.07582 0.00383 –0.00646 0.33443 –0.04506 0.96089 0.00750 0.26700 0.07594 0.00582 –0.00833 0.34924 –0.04512 0.94133 0.01053 0.25381 0.07597 0.00815 –0.01009 0.36430 –0.04510 0.92180 0.01349 0.24090 0.07590 0.01083 –0.01172 0.37961 –0.04500 0.90230 0.01639 0.22828 0.07573 0.01383 –0.01324 0.39516 –0.04482 0.88283 0.01923 0.21597 0.07547 0.01715 –0.01465 0.41094 –0.04456 0.86341 0.02201 0.20395 0.07512 0.02079 –0.01597 0.42696 –0.04422 0.84403 0.02473 0.19218 0.07467 0.02475 –0.01721 0.44319 –0.04381 0.82472 0.02739 0.18060 0.07411 0.02900 –0.01837 0.45964 –0.04332 0.80548 0.02999 0.16924 0.07342 0.03356 –0.01946 0.47630 –0.04275 0.78631 0.03253 0.15812 0.07257 0.03841 –0.02050 0.49317 –0.04211 0.76721 0.03501 0.14724 0.07156 0.04355 –0.02149 0.51023 –0.04141 0.74821 0.03743 0.13665 0.07038 0.04899 –0.02245 0.52748 –0.04063 0.72931 0.03979 0.12634 0.06901 0.05471 –0.02338 0.54491 –0.03978 0.71050 0.04209 0.11635 0.06746 0.06073 –0.02428 0.56252 –0.03886 0.69181 0.04433 0.10669 0.06573 0.06704 –0.02518 0.58030 –0.03788 0.67324 0.04650 0.09738 0.06381 0.07364 –0.02608 0.59824 –0.03683 0.65479 0.04861 0.08843 0.06172 0.08055 –0.02698 0.61634 –0.03572 0.63647 0.05065 0.07987 0.05946 0.08776 –0.02789 0.63459 –0.03455 0.61829 0.05263 0.07169 0.05705 0.09528 –0.02881 0.65298 –0.03332 0.60026 0.05453 0.06393 0.05449 0.10312 –0.02976 0.67150 –0.03203 0.58238 0.05637 0.05658 0.05181 0.11129 –0.03072 0.69016 –0.03068 0.56466 0.05814 0.04966 0.04901 0.11980 –0.03171 0.70893 –0.02927 0.54711 0.05983 0.04317 0.04612 0.12866 –0.03272 0.72781 –0.02780 0.52973 0.06145 0.03713 0.04316 0.13788 –0.03375 0.74681 –0.02628 0.51253 0.06299 0.03154 0.04013 0.14748 –0.03479 0.76589 –0.02470 0.49552 0.06445 0.02639 0.03706 0.15745 –0.03585 0.78508 –0.02306 0.47870 0.06583 0.02170 0.03397 0.16782 –0.03690 0.80434 –0.02137 0.46208 0.06713 0.01747 0.03087 0.17860 –0.03794 0.82368 –0.01962 0.44567 0.06834 0.01368 0.02778 0.18979 –0.03895 0.84310 –0.01782 0.42947 0.06948 0.01035 0.02471 0.20141 –0.03991 0.86257 –0.01596 0.41348 0.07052 0.00747 0.02169 0.21340 –0.04079 0.88209 –0.01404 0.39773 0.07148 0.00503 0.01871 0.22569 –0.04159 0.90167 –0.01206 0.38220 0.07234 0.00304 0.01579 0.23829 –0.04231 0.92128 –0.01003 0.36691 0.07312 0.00148 0.01295 0.25118 –0.04295 0.94093 –0.00793 0.35187 0.07380 0.00035 0.01019 0.26436 –0.04351 0.96059 –0.00577 0.33707 0.07439 –0.00036 0.00751 0.27782 –0.04398 0.98028 –0.00355 0.32252 0.07489 –0.00052 0.00241 0.29157 –0.04438 1.00000 –0.00126 0.30824 0.07530 0.00091 –0.00229 0.30559 –0.04468 NASA/TP—2016-218348 15

Appendix C.—Model Pressure Tap Locations

IRT Models TABLE C . 1. — PRESSURE TAP LOCATIONS FOR IRT SUBSCALE 18 - in. (45.7 - cm) CHORD, NACA 23012 MODEL Tap no. x / c y / c x, y , x , y , in. in. mm mm 1 0.90000 –0.01223 16.2000 –0.220 411.48 –5.59 2 0.80000 –0.02175 14.4000 –0.392 365.76 –9.95 3 0.70000 –0.02994 12.6000 –0.539 320.04 –13.69 4 0.60000 –0.03673 10.8000 –0.661 274.32 –16.79 5 0.50000 –0.04183 9.0000 –0.753 228.60 –19.12 6 0.40000 –0.04474 7.2000 –0.805 182.88 –20.45 7 0.30000 –0.04456 5.4000 –0.802 137.16 –20.37 8 0.25000 –0.04290 4.5000 –0.772 114.30 –19.61 9 0.20000 –0.03979 3.6000 –0.716 91.44 –18.19 10 0.15000 –0.03507 2.7000 –0.631 68.58 –16.03 11 0.12500 –0.03231 2.2500 –0.582 57.15 –14.77 12 0.10000 –0.02938 1.8000 –0.529 45.72 –13.43 13 0.07500 –0.02626 1.3500 –0.473 34.29 –12.00 14 0.05000 –0.02261 0.9000 –0.407 22.86 –10.34 15 0.04000 –0.02081 0.7200 –0.375 18.29 –9.51 16 0.03000 –0.01861 0.5400 –0.335 13.72 –8.51 17 0.02000 –0.01569 0.3600 –0.282 9.14 –7.17 18 0.01000 –0.01121 0.1800 –0.202 4.57 –5.13 19 0.00500 –0.00756 0.0900 –0.136 2.29 –3.46 20 0.00000 0.00000 0.0000 0.000 0.00 0.00 21 0.00250 0.01866 0.0450 0.336 1.14 8.53 22 0.01000 0.02434 0.1800 0.438 4.57 11.13 23 0.01500 0.02885 0.2700 0.519 6.86 13.19 24 0.02000 0.03272 0.3600 0.589 9.14 14.96 25 0.02500 0.03614 0.4500 0.651 11.43 16.52 26 0.03000 0.03921 0.5400 0.706 13.72 17.93 27 0.04000 0.04456 0.7200 0.802 18.29 20.37 28 0.05000 0.04915 0.9000 0.885 22.86 22.47 29 0.07500 0.05802 1.3500 1.044 34.29 26.53 30 0.10000 0.06435 1.8000 1.158 45.72 29.42 31 0.12500 0.06880 2.2500 1.238 57.15 31.46 32 0.15000 0.07182 2.7000 1.293 68.58 32.84 33 0.20000 0.07497 3.6000 1.349 91.44 34.28 34 0.25000 0.07595 4.5000 1.367 114.30 34.72 35 0.30000 0.07552 5.4000 1.359 137.16 34.53 36 0.35000 0.07388 6.3000 1.330 160.02 33.78 37 0.40000 0.07134 7.2000 1.284 182.88 32.62 38 0.45000 0.06802 8.1000 1.224 205.74 31.10 39 0.50000 0.06406 9.0000 1.153 228.60 29.29 40 0.55000 0.05955 9.9000 1.072 251.46 27.23 41 0.60000 0.05456 10.8000 0.982 274.32 24.95 42 0.65000 0.04914 11.7000 0.885 297.18 22.47 43 0.70000 0.04335 12.6000 0.780 320.04 19.82 44 0.75000 0.03720 13.5000 0.670 342.90 17.01 45 0.80000 0.03071 14.4000 0.553 365.76 14.04 46 0.85000 0.02389 15.3000 0.430 388.62 10.92 47 0.90000 0.01673 16.2000 0.301 411.48 7.65 48 0.95000 0.00919 17.1000 0.165 434.34 4.20 NASA/TP—2016-218348 17 TABLE C.2.—PRESSURE TAP LOCATIONS FOR IRT FULL-SCALE 72-in. (182.9-cm) CHORD, NACA 23012 MODEL Tap no. x / c y / c x , y , x , y , in. in. mm mm 1 1.0000 0.0000 72.000 0.000 1828.80 0.00 2 0.9750 0.0053 70.200 0.378 1783.08 9.60 3 0.9500 0.0092 68.400 0.662 1737.36 16.81 4 0.9250 0.0130 66.600 0.936 1691.64 23.77 5 0.9000 0.0167 64.800 1.204 1645.92 30.58 6 0.8500 0.0239 61.200 1.720 1554.48 43.69 7 0.8000 0.0307 57.600 2.212 1463.04 56.18 8 0.7500 0.0372 54.000 2.679 1371.60 68.05 9 0.7000 0.0433 50.400 3.121 1280.16 79.27 10 0.6500 0.0492 46.800 3.539 1188.72 89.89 11 0.6000 0.0546 43.200 3.928 1097.28 99.77 12 0.5500 0.0596 39.600 4.288 1005.84 108.92 13 0.5000 0.0641 36.000 4.613 914.40 117.17 14 0.4500 0.0680 32.400 4.898 822.96 124.41 15 0.4000 0.0713 28.800 5.137 731.52 130.48 16 0.3600 0.0734 25.920 5.288 658.37 134.32 17 0.3200 0.0750 23.040 5.398 585.22 137.11 18 0.2800 0.0758 20.160 5.460 512.06 138.68 19 0.2400 0.0759 17.280 5.464 438.91 138.79 20 0.2100 0.0753 15.120 5.422 384.05 137.72 21 0.1800 0.0741 12.960 5.334 329.18 135.48 22 0.1500 0.0718 10.800 5.172 274.32 131.37 23 0.1200 0.0681 8.640 4.900 219.46 124.46 24 0.0900 0.0621 6.480 4.471 164.59 113.56 25 0.0653 0.0549 4.698 3.950 119.33 100.33 26 0.0400 0.0446 2.880 3.210 73.15 81.53 27 0.0200 0.0328 1.440 2.359 36.58 59.92 28 0.0100 0.0244 0.720 1.754 18.29 44.55 29 0.0041 0.0173 0.293 1.246 7.44 31.65 30 0.0001 0.0091 0.004 0.654 0.10 16.61 31 0.0000 0.0000 0.000 0.000 0.00 0.00 32 0.0040 –0.0066 0.288 –0.478 7.32 –12.14 33 0.0100 –0.0113 0.720 –0.810 18.29 –20.57 34 0.0200 –0.0157 1.440 –1.130 36.58 –28.70 35 0.0350 –0.0198 2.520 –1.424 64.01 –36.17 36 0.0550 –0.0234 3.960 –1.686 100.58 –42.82 37 0.0750 –0.0263 5.400 –1.890 137.16 –48.01 38 0.1000 –0.0294 7.200 –2.116 182.88 –53.75 39 0.1500 –0.0351 10.800 –2.525 274.32 –64.14 40 0.2000 –0.0398 14.400 –2.865 365.76 –72.77 41 0.2500 –0.0429 18.000 –3.089 457.20 –78.46 42 0.3000 –0.0446 21.600 –3.209 548.64 –81.51 43 0.3500 –0.0451 25.200 –3.249 640.08 –82.52 44 0.4000 –0.0448 28.800 –3.222 731.52 –81.84 45 0.4500 –0.0436 32.400 –3.140 822.96 –79.76 46 0.5500 –0.0395 39.600 –2.845 1005.84 –72.26 47 0.6500 –0.0335 46.800 –2.414 1188.72 –61.32 48 0.7500 –0.0260 54.000 –1.873 1371.60 –47.57 49 0.8500 –0.0172 61.200 –1.236 1554.48 –31.39 50 0.9500 –0.0069 68.400 –0.500 1737.36 –12.70 NASA/TP—2016-218348 18 F1 Model TABLE C . 3. — PRESSURE TAP LOCATIONS FOR F1 NACA 23012 MODEL: CLEAN MODEL Surface Tap x / c y / c z / b x , y , z , x , y , z , no. in. in. in. mm mm mm (a) Chordwise row Lower 1 1.000000 –0.000358 0.436839 72.000 –0.026 60.057 1828.20 –0.65 1525.44 2 0.949453 –0.006999 0.436158 68.361 –0.504 59.963 1735.79 –12.80 1523.06 3 0.900032 –0.012228 0.436599 64.802 –0.880 60.024 1645.44 –22.36 1524.60 4 0.849651 –0.017198 0.436640 61.175 –1.238 60.029 1553.33 –31.44 1524.74 5 0.799649 –0.021788 0.437475 57.575 –1.569 60.144 1461.92 –39.83 1527.66 6 0.749978 –0.026018 0.436610 53.998 –1.873 60.025 1371.11 –47.57 1524.64 7 0.700663 –0.029894 0.436470 50.448 –2.152 60.006 1280.95 –54.65 1524.15 8 0.649840 –0.033534 0.436575 46.788 –2.414 60.020 1188.04 –61.31 1524.52 9 0.599772 –0.036742 0.436756 43.184 –2.645 60.045 1096.50 –67.17 1525.15 10 0.549335 –0.039553 0.436423 39.552 –2.848 59.999 1004.29 –72.31 1523.99 11 0.499718 –0.041849 0.436453 35.980 –3.013 60.003 913.59 –76.51 1524.09 12 0.450108 –0.043609 0.436528 32.408 –3.140 60.014 822.89 –79.73 1524.35 13 0.399989 –0.044746 0.436546 28.799 –3.222 60.016 731.26 –81.80 1524.41 14 0.349252 –0.045117 0.436541 25.146 –3.248 60.016 638.50 –82.48 1524.40 15 0.299216 –0.044556 0.436178 21.544 –3.208 59.966 547.03 –81.46 1523.13 16 0.249900 –0.042893 0.436492 17.993 –3.088 60.009 456.87 –78.42 1524.23 Removable 17 0.200162 –0.039807 0.436497 14.412 –2.866 60.010 365.94 –72.78 1524.24 leading 18 0.150094 –0.035076 0.436378 10.807 –2.525 59.993 274.40 –64.13 1523.83 edge 19 0.100215 –0.029408 0.436269 7.216 –2.117 59.978 183.21 –53.76 1523.45 20 0.075167 –0.026279 0.435994 5.412 –1.892 59.941 137.42 –48.04 1522.49 21 0.050393 –0.022682 0.435994 3.628 –1.633 59.940 92.13 –41.47 1522.49 22 0.029649 –0.018532 0.436510 2.135 –1.334 60.011 54.20 –33.88 1524.29 23 0.018844 –0.015291 0.436153 1.357 –1.101 59.962 34.45 –27.95 1523.04 24 0.008148 –0.010084 0.435472 0.587 –0.726 59.869 14.90 –18.44 1520.66 25 0.002618 –0.005033 0.435365 0.189 –0.362 59.854 4.79 –9.20 1520.29 26 0.000071 –0.000228 0.436229 0.005 –0.016 59.973 0.13 –0.42 1523.31 27 –0.000633 0.005197 0.436395 –0.046 0.374 59.996 –1.16 9.50 1523.89 28 0.000538 0.010725 0.436345 0.039 0.772 59.989 0.98 19.61 1523.71 29 0.003108 0.015908 0.436345 0.224 1.145 59.989 5.68 29.08 1523.71 30 0.006009 0.019961 0.436406 0.433 1.437 59.997 10.99 36.49 1523.93 31 0.010252 0.024614 0.436346 0.738 1.772 59.989 18.74 45.00 1523.72 32 0.014368 0.028366 0.436267 1.035 2.042 59.978 26.27 51.86 1523.44 33 0.019984 0.032748 0.436280 1.439 2.358 59.980 36.53 59.87 1523.49 34 0.029792 0.039121 0.436332 2.145 2.817 59.987 54.47 71.52 1523.67 35 0.040508 0.044848 0.436448 2.917 3.229 60.003 74.06 81.99 1524.07 36 0.050523 0.049377 0.436485 3.638 3.555 60.008 92.37 90.27 1524.20 37 0.060780 0.053375 0.436512 4.376 3.843 60.012 111.12 97.58 1524.29 38 0.080207 0.059555 0.436320 5.775 4.288 59.985 146.63 108.88 1523.63 39 0.100078 0.064390 0.436442 7.206 4.636 60.002 182.96 117.72 1524.05 40 0.120291 0.068100 0.436395 8.661 4.903 59.996 219.92 124.50 1523.89 41 0.139699 0.070740 0.436308 10.058 5.093 59.984 255.40 129.33 1523.58 42 0.161164 0.072822 0.436310 11.604 5.243 59.984 294.64 133.13 1523.59 43 0.181168 0.074143 0.437415 13.044 5.338 60.136 331.21 135.55 1527.45 NASA/TP—2016-218348 19 TABLE C.3.—Concluded. PRESSURE TAP LOCATIONS FOR F1 NACA 23012 MODEL: CLEAN MODEL Tap x , y , z , x , y , z , Surface x / c y / c z / b no. in. in. in. mm mm mm Upper 44 0.200463 0.075000 0.436542 14.433 5.400 60.016 366.49 137.11 1524.40 45 0.220415 0.075578 0.436637 15.870 5.442 60.029 402.96 138.17 1524.73 46 0.241198 0.075899 0.436793 17.366 5.465 60.050 440.96 138.76 1525.28 47 0.260589 0.075966 0.436765 18.762 5.470 60.046 476.41 138.88 1525.18 48 0.280101 0.075827 0.436558 20.167 5.460 60.018 512.08 138.63 1524.46 49 0.299747 0.075495 0.436580 21.582 5.436 60.021 548.00 138.02 1524.53 50 0.320199 0.074964 0.436556 23.054 5.397 60.018 585.39 137.05 1524.45 51 0.340077 0.074282 0.436471 24.486 5.348 60.006 621.73 135.80 1524.15 52 0.360039 0.073441 0.436429 25.923 5.288 60.000 658.22 134.27 1524.01 53 0.379808 0.072468 0.436376 27.346 5.218 59.993 694.37 132.49 1523.82 54 0.400032 0.071340 0.436447 28.802 5.136 60.003 731.34 130.42 1524.07 55 0.419183 0.070155 0.436560 30.181 5.051 60.018 766.35 128.26 1524.46 56 0.439982 0.068749 0.436512 31.679 4.950 60.012 804.38 125.69 1524.30 57 0.459681 0.067310 0.436677 33.097 4.846 60.034 840.39 123.06 1524.87 58 0.479972 0.065727 0.436628 34.558 4.732 60.028 877.48 120.16 1524.70 59 0.500643 0.064015 0.435801 36.046 4.609 59.914 915.28 117.03 1521.82 60 0.518759 0.062435 0.436823 37.351 4.495 60.054 948.40 114.14 1525.38 61 0.540170 0.060482 0.436476 38.892 4.355 60.007 987.54 110.57 1524.17 62 0.560303 0.058563 0.436813 40.342 4.217 60.053 1024.35 107.06 1525.35 63 0.580485 0.056563 0.436320 41.795 4.073 59.985 1061.24 103.41 1523.63 64 0.600351 0.054524 0.436143 43.225 3.926 59.961 1097.56 99.68 1523.01 65 0.639920 0.050270 0.436922 46.074 3.619 60.068 1169.90 91.90 1525.73 66 0.679950 0.045719 0.436582 48.956 3.292 60.021 1243.08 83.58 1524.54 67 0.720134 0.040919 0.436464 51.850 2.946 60.005 1316.55 74.81 1524.13 68 0.760150 0.035915 0.436490 54.731 2.586 60.009 1389.71 65.66 1524.22 69 0.800202 0.030692 0.436501 57.615 2.210 60.010 1462.93 56.11 1524.26 70 0.850191 0.023871 0.436508 61.214 1.719 60.011 1554.32 43.64 1524.28 71 0.899308 0.016831 0.436459 64.750 1.212 60.004 1644.11 30.77 1524.11 72 0.949720 0.009239 0.435792 68.380 0.665 59.913 1736.28 16.89 1521.78 (b) Spanwise row Upper 3.119 79.20 77.0 73 0.700231 0.043324 0.022051 50.417 3.032 1280.16 74 0.699839 0.043371 0.043571 50.388 3.123 5.990 1279.45 79.29 152.1 75 0.699932 0.043360 0.065497 50.395 3.122 9.004 1279.62 79.27 228.7 76 0.699423 0.043420 0.087124 50.358 3.126 11.978 1278.68 79.38 304.2 77 0.700744 0.043263 0.116363 50.454 3.115 15.998 1281.10 79.09 406.3 78 0.700061 0.043344 0.145621 50.404 3.121 20.020 1279.85 79.24 508.5 79 0.700236 0.043323 0.174820 50.417 3.119 24.034 1280.17 79.20 610.5 80 0.698772 0.043498 0.217917 50.312 3.132 29.959 1277.49 79.52 761.0 81 0.700571 0.043283 0.262344 50.441 3.116 36.067 1280.78 79.13 916.1 82 0.700262 0.043320 0.305944 50.419 3.119 42.061 1280.22 79.20 1068.4 83 0.700345 0.043310 0.694142 50.425 3.118 95.431 1280.37 79.18 2423.9 84 0.700209 0.043327 0.737883 50.415 3.120 101.444 1280.12 79.21 2576.7 85 0.700058 0.043345 0.781435 50.404 3.121 107.432 1279.85 79.24 2728.8 86 0.700517 0.043290 0.825281 50.437 3.117 113.460 1280.69 79.14 2881.9 87 0.699998 0.043352 0.854412 50.400 3.121 117.465 1279.74 79.26 2983.6 88 0.700356 0.043309 0.883596 50.426 3.118 121.477 1280.39 79.18 3085.5 89 0.700428 0.043300 0.912702 50.431 3.118 125.478 1280.52 79.16 3187.1 90 0.700207 0.043327 0.934588 50.415 3.120 128.487 1280.12 79.21 3263.6 91 0.700718 0.043266 0.956310 50.452 3.115 131.473 1281.05 79.10 3339.4 92 0.700282 0.043318 0.978547 50.420 3.119 134.531 1280.25 79.19 3417.1 NASA/TP—2016-218348 20 TABLE C . 4. — PRESSURE TAP LOCATIO NS FOR F1 NACA 23012 MODEL: ICE SHAPE EG1 164, CHORDWISE ROW Surface Tap no. x / c y / c z / b x , y , z , x , y , z , in. in. in. mm mm mm Removable 17 0.195005 –0.039517 0.436427 14.040 –2.845 60.000 356.63 –72.27 1524.0 leading 18 0.149990 –0.034943 0.436427 10.799 –2.516 60.000 274.30 –63.90 1524.0 edge 19 0.109991 –0.030460 0.436427 7.919 –2.193 60.000 201.15 –55.71 1524.0 20 0.069972 –0.025641 0.436427 5.038 –1.846 60.000 127.97 –46.89 1524.0 21 0.039475 –0.021390 0.436427 2.842 –1.540 60.000 72.19 –39.12 1524.0 22 0.030549 –0.024686 0.436427 2.200 –1.777 60.000 55.87 –45.15 1524.0 23 0.028026 –0.021060 0.434187 2.018 –1.516 59.692 51.25 –38.52 1516.2 24 0.023797 –0.022508 0.436427 1.713 –1.621 60.000 43.52 –41.16 1524.0 25 0.019247 –0.017919 0.436427 1.386 –1.290 60.000 35.20 –32.77 1524.0 26 0.007081 –0.018019 0.436427 0.510 –1.297 60.000 12.95 –32.95 1524.0 27 0.003830 –0.010571 0.436427 0.276 –0.761 60.000 7.00 –19.33 1524.0 28 –0.000686 –0.003863 0.436427 –0.049 –0.278 60.000 –1.25 –7.07 1524.0 29 –0.007741 0.001039 0.437300 –0.557 0.075 60.120 –14.16 1.90 1527.0 30 –0.005374 0.008287 0.435991 –0.387 0.597 59.940 –9.83 15.15 1522.5 31 –0.009980 0.013909 0.436864 –0.719 1.001 60.060 –18.25 25.44 1525.5 32 –0.017845 0.017401 0.436427 –1.285 1.253 60.000 –32.63 31.82 1524.0 33 0.002359 0.013926 0.436427 0.170 1.003 60.000 4.31 25.47 1524.0 34 0.009898 0.023620 0.436427 0.713 1.701 60.000 18.10 43.20 1524.0 35 0.019976 0.032109 0.436427 1.438 2.312 60.000 36.53 58.72 1524.0 36 0.029967 0.038915 0.436427 2.158 2.802 60.000 54.80 71.17 1524.0 37 0.039980 0.044258 0.436427 2.879 3.187 60.000 73.12 80.94 1524.0 38 0.049992 0.048891 0.436427 3.599 3.520 60.000 91.43 89.41 1524.0 39 0.060006 0.052839 0.436427 4.320 3.804 60.000 109.74 96.63 1524.0 40 0.079985 0.059289 0.436427 5.759 4.269 60.000 146.28 108.43 1524.0 41 0.099996 0.064100 0.436427 7.200 4.615 60.000 182.87 117.23 1524.0 42 0.119999 0.067655 0.436427 8.640 4.871 60.000 219.45 123.73 1524.0 43 0.139996 0.070459 0.436427 10.080 5.073 60.000 256.02 128.86 1524.0 101 0.159999 0.072575 0.436427 11.520 5.225 60.000 292.61 132.72 1524.0 102 0.175000 0.073851 0.436427 12.600 5.317 60.000 320.04 135.06 1524.0 NASA/TP—2016-218348 21 TABLE C . 5. — PRESSURE TAP LOCATIO NS FOR F1 NACA 23012 MODEL: ICE SHAPE EG1 162, CHORDWISE ROW Surface Tap no. x / c y / c z / b x , y , z , x , y , z , in. in. in. mm mm mm Removable 17 0.195000 –0.039009 0.436427 14.040 –2.809 60.000 356.62 –71.34 1524.0 leading 18 0.150000 –0.034353 0.436427 10.800 –2.473 60.000 274.32 –62.82 1524.0 edge 19 0.108333 –0.029758 0.436427 7.800 –2.143 60.000 198.12 –54.42 1524.0 20 0.075000 –0.025846 0.436427 5.400 –1.861 60.000 137.16 –47.27 1524.0 21 0.050000 –0.022446 0.436427 3.600 –1.616 60.000 91.44 –41.05 1524.0 22 0.028308 –0.018889 0.436427 2.038 –1.360 60.000 51.77 –34.54 1524.0 23 0.019352 –0.016481 0.436427 1.393 –1.187 60.000 35.39 –30.14 1524.0 24 0.011971 –0.015238 0.436427 0.862 –1.097 60.000 21.89 –27.87 1524.0 25 0.005000 –0.012456 0.436427 0.360 –0.897 60.000 9.14 –22.78 1524.0 26 0.000000 –0.009740 0.436427 0.000 –0.701 60.000 0.00 –17.81 1524.0 27 –0.005000 –0.005713 0.436427 –0.360 –0.411 60.000 –9.14 –10.45 1524.0 28 –0.009162 –0.001112 0.436427 –0.660 –0.080 60.000 –16.76 –2.03 1524.0 29 –0.010000 0.004778 0.436427 –0.720 0.344 60.000 –18.29 8.74 1524.0 30 –0.007999 0.009863 0.436427 –0.576 0.710 60.000 –14.63 18.04 1524.0 31 –0.005000 0.015321 0.436427 –0.360 1.103 60.000 –9.14 28.02 1524.0 32 0.000056 0.020899 0.436427 0.004 1.505 60.000 0.10 38.22 1524.0 33 0.005000 0.026049 0.436427 0.360 1.876 60.000 9.14 47.64 1524.0 34 0.010000 0.029436 0.436427 0.720 2.119 60.000 18.29 53.83 1524.0 35 0.015000 0.032885 0.436427 1.080 2.368 60.000 27.43 60.14 1524.0 36 0.020372 0.036039 0.436427 1.467 2.595 60.000 37.26 65.91 1524.0 37 0.028971 0.040779 0.436427 2.086 2.936 60.000 52.98 74.58 1524.0 38 0.040000 0.045836 0.436427 2.880 3.300 60.000 73.15 83.82 1524.0 39 0.050000 0.049953 0.436427 3.600 3.597 60.000 91.44 91.35 1524.0 40 0.060000 0.053729 0.436427 4.320 3.868 60.000 109.73 98.26 1524.0 41 0.080000 0.059820 0.436427 5.760 4.307 60.000 146.30 109.40 1524.0 42 0.100000 0.064581 0.436427 7.200 4.650 60.000 182.88 118.11 1524.0 43 0.120000 0.067937 0.436427 8.640 4.891 60.000 219.46 124.24 1524.0 101 0.140000 0.070676 0.436427 10.080 5.089 60.000 256.03 129.25 1524.0 102 0.160000 0.072786 0.436427 11.520 5.241 60.000 292.61 133.11 1524.0 103 0.175000 0.074103 0.436427 12.600 5.335 60.000 320.04 135.52 1524.0 NASA/TP—2016-218348 22 TABLE C . 6. — PRESSURE TAP LOCATIO NS FOR F1 NACA 23012 MODEL: ICE SHAPE EG1 126, CHORDWISE ROW Surface Tap no. x / c y / c z / b x , y , z , x , y , z , in. in. in. mm mm mm Removable 17 0.194992 –0.039814 0.436427 14.039 –2.867 60.000 356.60 –72.81 1524.00 leading 18 0.150008 –0.034844 0.436427 10.801 –2.509 60.000 274.34 –63.72 1524.00 edge 19 0.108339 –0.030230 0.436427 7.800 –2.177 60.000 198.13 –55.28 1524.00 20 0.074970 –0.026334 0.436427 5.398 –1.896 60.000 137.10 –48.16 1524.00 21 0.049923 –0.022895 0.436427 3.594 –1.648 60.000 91.30 –41.87 1524.00 22 0.029227 –0.019032 0.436427 2.104 –1.370 60.000 53.45 –34.81 1524.00 23 0.019182 –0.016224 0.436427 1.381 –1.168 60.000 35.08 –29.67 1524.00 24 0.011530 –0.013282 0.436427 0.830 –0.956 60.000 21.09 –24.29 1524.00 25 0.005831 –0.010180 0.436427 0.420 –0.733 60.000 10.66 –18.62 1524.00 26 0.001644 –0.005675 0.436427 0.118 –0.409 60.000 3.01 –10.38 1524.00 27 –0.000831 –0.000705 0.436427 –0.060 –0.051 60.000 –1.52 –1.29 1524.00 28 –0.001408 0.004444 0.436427 –0.101 0.320 60.000 –2.57 8.13 1524.00 29 –0.000744 0.009170 0.436427 –0.054 0.660 60.000 –1.36 16.77 1524.00 30 0.000956 0.013801 0.436427 0.069 0.994 60.000 1.75 25.24 1524.00 31 0.003488 0.017423 0.436427 0.251 1.254 60.000 6.38 31.86 1524.00 32 0.006699 0.021686 0.436427 0.482 1.561 60.000 12.25 39.66 1524.00 33 0.010625 0.024972 0.436427 0.765 1.798 60.000 19.43 45.67 1524.00 34 0.014732 0.028634 0.436427 1.061 2.062 60.000 26.94 52.37 1524.00 35 0.020428 0.032949 0.436427 1.471 2.372 60.000 37.36 60.26 1524.00 36 0.030251 0.039281 0.436427 2.178 2.828 60.000 55.32 71.84 1524.00 37 0.040185 0.044455 0.436427 2.893 3.201 60.000 73.49 81.30 1524.00 38 0.050125 0.048934 0.436427 3.609 3.523 60.000 91.67 89.49 1524.00 39 0.060214 0.052753 0.436427 4.335 3.798 60.000 110.12 96.47 1524.00 40 0.080133 0.059168 0.436427 5.770 4.260 60.000 146.55 108.21 1524.00 41 0.100082 0.063981 0.436427 7.206 4.607 60.000 183.03 117.01 1524.00 42 0.120048 0.067668 0.436427 8.643 4.872 60.000 219.54 123.75 1524.00 43 0.140044 0.070467 0.436427 10.083 5.074 60.000 256.11 128.87 1524.00 101 0.160031 0.072630 0.436427 11.522 5.229 60.000 292.66 132.83 1524.00 102 0.175013 0.074027 0.436427 12.601 5.330 60.000 320.06 135.38 1524.00 NASA/TP—2016-218348 23 TABLE C . 7. — PRESSURE TAP LOCATIO NS FOR F1 NACA 23012 MODEL: ICE SHAPE EG1 159, CHORDWISE ROW Surface Tap no. x / c y / c z / b x , y , z , x , y , z , in. in. in. mm mm mm Removable 17 0.195000 –0.039 651 0.436427 14.040 –2.855 60.000 356.62 –72.51 1524.0 leading 18 0.170000 –0.036797 0.436427 12.240 –2.649 60.000 310.90 –67.30 1524.0 edge 19 0.150000 –0.034731 0.436587 10.800 –2.501 60.022 274.32 –63.52 1524.6 20 0.127580 –0.032850 0.436427 9.186 –2.365 60.000 233.32 –60.08 1524.0 21 0.118031 –0.032606 0.437445 8.498 –2.348 60.140 215.86 –59.63 1527.6 22 0.107611 –0.035434 0.436427 7.748 –2.551 60.000 196.80 –64.80 1524.0 23 0.102335 –0.029786 0.436427 7.368 –2.145 60.000 187.15 –54.47 1524.0 24 0.095153 –0.027734 0.436427 6.851 –1.997 60.000 174.02 –50.72 1524.0 25 0.076012 –0.025660 0.436427 5.473 –1.848 60.000 139.01 –46.93 1524.0 26 0.053969 –0.022696 0.436427 3.886 –1.634 60.000 98.70 –41.51 1524.0 27 0.032151 –0.018725 0.436427 2.315 –1.348 60.000 58.80 –34.24 1524.0 28 0.021302 –0.015659 0.436427 1.534 –1.127 60.000 38.96 –28.64 1524.0 29 0.012655 –0.012367 0.436427 0.911 –0.890 60.000 23.14 –22.62 1524.0 30 0.005730 –0.007883 0.436427 0.413 –0.568 60.000 10.48 –14.42 1524.0 31 0.000772 –0.001282 0.436427 0.056 –0.092 60.000 1.41 –2.34 1524.0 32 –0.000304 0.006847 0.436427 –0.022 0.493 60.000 –0.56 12.52 1524.0 33 0.002484 0.014646 0.436427 0.179 1.055 60.000 4.54 26.78 1524.0 34 0.008106 0.022520 0.436427 0.584 1.621 60.000 14.82 41.18 1524.0 35 0.016324 0.030212 0.436427 1.175 2.175 60.000 29.85 55.25 1524.0 36 0.024160 0.035698 0.436427 1.739 2.570 60.000 44.18 65.28 1524.0 37 0.031322 0.039864 0.436427 2.255 2.870 60.000 57.28 72.90 1524.0 38 0.037411 0.043110 0.436427 2.694 3.104 60.000 68.42 78.84 1524.0 39 0.043611 0.045980 0.436427 3.140 3.311 60.000 79.76 84.09 1524.0 40 0.048795 0.049268 0.436427 3.513 3.547 60.000 89.24 90.10 1524.0 41 0.044035 0.057644 0.436427 3.171 4.150 60.000 80.53 105.42 1524.0 42 0.044244 0.060759 0.437045 3.186 4.375 60.085 80.91 111.12 1526.2 43 0.060000 0.053924 0.435809 4.320 3.883 59.915 109.73 98.62 1521.8 101 0.070000 0.056589 0.436427 5.040 4.074 60.000 128.02 103.49 1524.0 102 0.080000 0.059704 0.436704 5.760 4.299 60.038 146.30 109.19 1525.0 103 0.090000 0.062270 0.436856 6.480 4.483 60.059 164.59 113.88 1525.5 104 0.100000 0.064411 0.436856 7.200 4.638 60.059 182.88 117.80 1525.5 105 0.110000 0.066143 0.436427 7.920 4.762 60.000 201.17 120.96 1524.0 106 0.120000 0.067665 0.436427 8.640 4.872 60.000 219.46 123.75 1524.0 107 0.140000 0.070380 0.436427 10.080 5.067 60.000 256.03 128.71 1524.0 108 0.160000 0.072540 0.436427 11.520 5.223 60.000 292.61 132.66 1524.0 109 0.175000 0.073853 0.436427 12.600 5.317 60.000 320.04 135.06 1524.0 NASA/TP—2016-218348 24 TABLE C . 8. — PRESSURE TAP LOCATIO NS FOR F1 NACA 23012 MODEL: ICE SHAPE EG1 125, CHORDWISE ROW Surface Tap no. x / c y / c z / b x , y , z , x , y , z , in. in. in. mm mm mm Removable 17 0.195000 –0.039569 0.436427 14.040 –2.849 60.000 356.62 –72.36 1524.0 leading 18 0.150000 –0.034415 0.436427 10.800 –2.478 60.000 274.32 –62.94 1524.0 edge 19 0.108333 –0.029675 0.436427 7.800 –2.137 60.000 198.12 –54.27 1524.0 20 0.075000 –0.025478 0.436427 5.400 –1.834 60.000 137.16 –46.59 1524.0 21 0.050000 –0.021830 0.436427 3.600 –1.572 60.000 91.44 –39.92 1524.0 22 0.030000 –0.017950 0.436427 2.160 –1.292 60.000 54.86 –32.83 1524.0 23 0.019832 –0.015303 0.436427 1.428 –1.102 60.000 36.27 –27.99 1524.0 24 0.009722 –0.011920 0.436427 0.700 –0.858 60.000 17.78 –21.80 1524.0 25 0.003001 –0.009511 0.435809 0.216 –0.685 59.915 5.49 –17.39 1521.8 26 –0.004231 –0.005423 0.437045 –0.305 –0.390 60.085 –7.74 –9.92 1526.2 27 –0.008713 0.000263 0.437045 –0.627 0.019 60.085 –15.93 0.48 1526.2 28 –0.007442 0.008811 0.437045 –0.536 0.634 60.085 –13.61 16.11 1526.2 29 –0.002336 0.013758 0.436427 –0.168 0.991 60.000 –4.27 25.16 1524.0 30 0.003486 0.018993 0.436245 0.251 1.367 59.975 6.38 34.73 1523.4 31 0.007976 0.023645 0.436427 0.574 1.702 60.000 14.59 43.24 1524.0 32 0.013605 0.028862 0.436427 0.980 2.078 60.000 24.88 52.78 1524.0 33 0.020000 0.033827 0.436427 1.440 2.436 60.000 36.58 61.86 1524.0 34 0.030000 0.040181 0.436427 2.160 2.893 60.000 54.86 73.48 1524.0 35 0.040000 0.045437 0.436427 2.880 3.271 60.000 73.15 83.10 1524.0 36 0.050000 0.049838 0.436427 3.600 3.588 60.000 91.44 91.14 1524.0 37 0.060000 0.053761 0.436427 4.320 3.871 60.000 109.73 98.32 1524.0 38 0.080000 0.059923 0.436427 5.760 4.314 60.000 146.30 109.59 1524.0 39 0.100000 0.064650 0.436427 7.200 4.655 60.000 182.88 118.23 1524.0 40 0.120000 0.068298 0.436427 8.640 4.917 60.000 219.46 124.90 1524.0 41 0.140000 0.070944 0.436427 10.080 5.108 60.000 256.03 129.74 1524.0 42 0.160000 0.073057 0.436427 11.520 5.260 60.000 292.61 133.61 1524.0 43 0.175000 0.074258 0.436427 12.600 5.347 60.000 320.04 135.80 1524.0 NASA/TP—2016-218348 25 TABLE C . 9. — PRESSURE TAP LOCATIONS FOR F1 NAC A 23012 MODEL: ICE S HAPE EG1134, CHORDWI SE ROW Surface Tap x / c y / c z / b x , y , z , x , y , z , no. in. in. in. mm mm mm Removable 17 0.195009 –0.039737 0.436427 14.041 –2.861 60.000 356.63 –72.67 1524.00 leading 18 0.149992 –0.034916 0.436427 10.799 –2.514 60.000 274.31 –63.85 1524.00 edge 19 0.108339 –0.030228 0.436427 7.800 –2.176 60.000 198.13 –55.28 1524.00 20 0.075039 –0.026056 0.436427 5.403 –1.876 60.000 137.23 –47.65 1524.00 21 0.050078 –0.022414 0.436427 3.606 –1.614 60.000 91.58 –40.99 1524.00 22 0.030437 –0.018880 0.436427 2.191 –1.359 60.000 55.66 –34.53 1524.00 23 0.023336 –0.017082 0.436427 1.680 –1.230 60.000 42.68 –31.24 1524.00 24 0.014289 –0.013887 0.436427 1.029 –1.000 60.000 26.13 –25.40 1524.00 25 0.006806 –0.010363 0.436427 0.490 –0.746 60.000 12.45 –18.95 1524.00 26 0.001751 –0.006514 0.436427 0.126 –0.469 60.000 3.20 –11.91 1524.00 27 –0.002172 –0.000837 0.436427 –0.156 –0.060 60.000 –3.97 –1.53 1524.00 28 –0.002927 0.005025 0.436427 –0.211 0.362 60.000 –5.35 9.19 1524.00 29 –0.001904 0.009904 0.436427 –0.137 0.713 60.000 –3.48 18.11 1524.00 30 0.001379 0.015966 0.436427 0.099 1.150 60.000 2.52 29.20 1524.00 31 0.004846 0.020382 0.436427 0.349 1.468 60.000 8.86 37.28 1524.00 32 0.008899 0.024700 0.436427 0.641 1.778 60.000 16.28 45.17 1524.00 33 0.013671 0.028886 0.436427 0.984 2.080 60.000 25.00 52.83 1524.00 34 0.019680 0.033198 0.436427 1.417 2.390 60.000 35.99 60.71 1524.00 35 0.029751 0.039591 0.436427 2.142 2.851 60.000 54.41 72.40 1524.00 36 0.039883 0.044734 0.436427 2.872 3.221 60.000 72.94 81.81 1524.00 37 0.049888 0.049166 0.436427 3.592 3.540 60.000 91.24 89.91 1524.00 38 0.059812 0.053212 0.436427 4.306 3.831 60.000 109.38 97.31 1524.00 39 0.079864 0.059624 0.436427 5.750 4.293 60.000 146.06 109.04 1524.00 40 0.099925 0.064315 0.436427 7.195 4.631 60.000 182.74 117.62 1524.00 41 0.119950 0.067959 0.436427 8.636 4.893 60.000 219.36 124.28 1524.00 42 0.139960 0.070836 0.436427 10.077 5.100 60.000 255.96 129.55 1524.00 43 0.159975 0.072984 0.436427 11.518 5.255 60.000 292.56 133.47 1524.00 101 0.174990 0.074204 0.436427 12.599 5.343 60.000 320.02 135.70 1524.00 NASA/TP—2016-218348 26

Appendix D.—Test Matrices

IRT Test Matrices TABLE D.1.—IRT 18-in. (457-m) CHORD, SUBSCALE MODEL TESTS Run V , AoA , MVD , LWC , T t , T s , Exposure Ice shape type and run notes kt deg. μm g/m °F (°C) °F (°C) time, min.

ED0711 250 2.0 15.4 0.67 20.0 (–6.7) 5.2 (–14.9) 10.0 Horn ED0712 250 2.0 15.4 0.67 24.0 (–4.4) 9.8 (–12.3) 10.0 Horn ED0713 175 5.3 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 10.0 Horn ED0714 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 10.0 Horn ED0715 175 5.3 15.0 0.64 30.0 (–1.1) 22.8 (–5.1) 10.0 Horn ED0716 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 10.0 Horn, repeat 714 ED0717 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 10.0 Horn, repeat 716, mold ED0718 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 5.0 Horn ED0719 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 2.0 Roughness ED0720 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 0.5 Roughness ED0721 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 5.0 Horn, repeat 718, mold ED0722 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 1.0 Roughness ED0723 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 0.5 Roughness, repeat 720, mold ED0724 250 2.0 15.0 0.33 8.0 (–13.3) –7.1 (–21.7) 10.0 Streamwise ED0725 250 2.0 15.0 0.33 8.0 (–13.3) –7.1 (–21.7) 5.0 Streamwise ED0726 250 2.0 15.0 0.33 8.0 (–13.3) –7.1 (–21.7) 5.0 Streamwise, repeat 725, mold ED0727 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 10.0 Streamwise ED0728 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 5.0 Streamwise ED0729 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 1.0 Roughness ED0730 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 5.0 Streamwise, repeat 728, mold ED0731 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 2.0 Roughness ED0732 250 2.0 15.4 0.67 28.0 (–2.2) 11.0 (–10.5) 5.0 Horn ED0733 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 5.0 Horn ED0734 200 2.0 17.6 1.06 28.0 (–2.2) 18.5 (–7.5) 5.0 Horn ED0735 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 5.0 Horn, repeat 733, mold ED0736 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 0.5 Roughness, repeat 720 ED0737 175 5.3 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 10.0 Horn, repeat 713, mold ED0738 250 2.0 15.0 0.33 8.0 (–13.3) –7.1 (–21.7) 5.0 Streamwise, repeat 725 ED0739 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 1.0 Roughness, repeat 729 ED0740 250 2.0 15.4 0.67 24.0 (–4.4) 9.8 (–12.3) 10.5 Spanwise ridge ED0741 175 0.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 15.0 Spanwise ridge ED0742 175 0.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 10.0 Spanwise ridge ED0743 175 0.0 15.0 0.64 15.0 (–9.4) 7.8 (–13.5) 5.0 Spanwise ridge ED0744 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 0.5 Roughness, repeat 720 ED0745 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 2.0 Roughness ED0746 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 0.5 Roughness NASA/TP—2016-218348 27 TABLE D.1.—Concluded. IRT 18-in. (457-m) CHORD, SUBSCALE MODEL TESTS Run V , AoA , MVD , LWC , T t , T s , Exposure Ice shape type and run notes kt deg. μm g/m °F (°C) °F (°C) time, min.

ED0747 250 2.0 15.4 0.67 28.0 (–2.2) 22.0 (–10.5) 0.5 Roughness ED0748 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 1.0 Roughness, repeat 729, mold ED0749 175 0.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge ED0750 175 0.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge, repeat 749 ED0751 175 0.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge, repeat 749, mold ED0752 250 2.0 15.0 0.33 8.0 (–13.3) –7.1 (–21.7) 1.0 Roughness ED0753 200 2.0 15.0 0.39 8.0 (–13.3) –1.3 (–18.5) 1.0 Roughness ED0754 200 2.0 30.0 0.40 8.0 (–13.3) –1.3 (–18.5) 5.0 Streamwise ED0755 175 5.3 30.0 0.44 0.0 (–17.8) –7.4 (–21.8) 5.0 Streamwise ED0756 200 2.0 30.0 0.40 0.0 (–17.8) –9.6 (–23.1) 5.0 Streamwise, mold ED0757 200 2.0 15.0 0.33 0.0 (–17.8) –9.6 (–23.1) 10.0 Streamwise, mold ED0758 175 0.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge ED0759 175 0.9 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge ED0760 175 0.9 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge, repeat 759, mold ED0761 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 5.0 Horn, repeat 735 ED0762 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 0.5 Roughness, repeat 746, mold ED0763 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 5.0 Horn/repeat 718 ED0764 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 2.0 Roughness, repeat 719, mold ED0765 175 1.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge ED0766 175 1.0 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 5.0 Spanwise ridge, repeat 765, mold ED0767 175 5.3 15.0 0.64 24.0 (–4.4) 16.8 (–8.5) 10.0 Horn, repeat 713 and 737 ED0768 175 5.3 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 2.0 Roughness, repeat 719 and 764 ED0769 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 0.5 Roughness, repeat 746 and 762 ED0770 200 2.0 30.0 0.40 0.0 (–17.8) –9.6 (–23.1) 5.0 Streamwise, repeat 756 ED0771 200 2.0 15.0 0.33 0.0 (–17.8) –9.6 (–23.1) 10.0 Streamwise, repeat 757 ED0772 175 5.3 15.0 0.30 0.0 (–17.8) –7.4 (–21.8) 5.0 Streamwise, repeat 728 and 730 ED0773 200 2.0 15.4 0.75 28.0 (–2.2) 18.5 (–7.5) 10.0 Horn/mold NASA/TP—2016-218348 28 TABLE D.2.—IRT 72-in.- (1829-mm-) CHORD, FULL-SCALE MODEL TESTS Run V , AoA , MVD , LWC , T t , T s , Exposure Ice shape type and run notes kt deg. μm g/m °F (°C) °F (°C) time, min.

EG1109 175 5.0 20.0 0.50 20.0 (–6.7) 12.8 (–10.7) 22.5 Horn EG1110 175 5.0 20.0 0.50 24.0 (–4.4) 16.8 (–8.4) 22.5 Horn EG1111 175 5.0 20.0 0.50 28.0 (–2.2) 20.8 (–6.2) 22.5 Horn EG1112 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 22.5 Horn EG1113 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 22.5 Horn, repeat 1112 EG1114 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 22.5 Horn, repeat 1112, mold EG1115 175 5.0 20.0 0.60 28.0 (–2.2) 20.8 (–6.2) 22.5 Horn EG1116 175 5.0 20.0 0.60 30.0 (–1.1) 22.7 (–5.2) 22.5 Horn EG1117 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 2.0 Roughness EG1118 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 1.0 Roughness EG1119 175 5.0 20.0 0.60 28.0 (–2.2) 20.8 (–6.2) 2.0 Roughness EG1120 200 2.0 20.0 0.30 4.0 (–15.6) –5.3 (–20.7) 10.0 Streamwise EG1121 200 2.0 40.0 0.55 4.0 (–15.6) –5.3 (–20.7) 10.0 Streamwise EG1122 200 2.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 10.0 Streamwise EG1123 200 2.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 20.0 Streamwise EG1124 200 5.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 20.0 Streamwise EG1125 200 2.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 20.0 Streamwise, repeat 1123, mold EG1126 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 2.0 Roughness, repeat 1117, mold EG1127 175 5.0 20.0 0.70 28.0 (–2.2) 20.8 (–6.2) 22.5 Horn EG1128 175 5.0 20.0 0.85 28.0 (–2.2) 20.8 (–6.2) 22.5 Horn EG1129 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 22.5 Horn, repeat 1112 and 1113 EG1130 175 5.0 20.0 0.85 28.0 (–2.2) 20.8 (–6.2) 22.5 Horn, repeat 1128, mold EG1131 200 2.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 2.0 Roughness EG1132 200 2.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 4.0 Roughness EG1133 200 2.0 40.0 0.55 4.0 (–15.6) –5.3 (–20.7) 2.0 Roughness EG1134 200 2.0 40.0 0.55 4.0 (–15.6) –5.3 (–20.7) 2.0 Roughness, repeat 1133, mold EG1135 200 2.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 20.0 Streamwise, repeat 1123 and 1125 EG1136 200 2.0 40.0 0.55 4.0 (–15.6) –5.3 (–20.7) 5.0 Streamwise EG1137 200 5.0 15.0 0.30 4.0 (–15.6) –5.3 (–20.7) 20.0 Streamwise, repeat 1124, mold EG1138 175 5.0 20.0 0.85 28.0 (–2.2) 20.8 (–6.2) 22.5 Horn, repeat 1128 and 1130 EG1139 175 5.0 20.0 0.85 28.0 (–2.2) 20.8 (–6.2) 11.25 Horn EG1140 200 2.0 20.0 0.50 28.0 (–2.2) 18.7 (–7.4) 2.0 Roughness, repeat 1117, 1126 EG1141 200 2.0 30.0 0.45 4.0 (–15.6) –5.3 (–20.7) 10.0 Streamwise EG1142 200 2.0 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge EG1143 200 0.0 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge EG1144 200 1.0 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge EG1145 200 1.5 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge a EG1146 200 1.5 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge b EG1147 200 0/2/1.5 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge a EG1148 200 1.5 20.0 0.50 20.0 (–6.7) 10.7 (–11.8) 15.0 Spanwise ridge a Multiple runs at the same icing conditions were at various heater settings and resulted in varying spanwise ridge ice accretions.

b 5 min at each AoA .

NASA/TP—2016-218348 29 TABLE D.2.—Concluded. IRT 72-in.- (1829-mm-) CHORD, FULL-SCALE MODEL TESTS Run V , AoA , MVD , LWC , T t , T s , Exposure Ice shape type and run notes kt deg. μm g/m °F (°C) °F (°C) time, min.

EG1149 150 1.5 20.0 0.62 20.0 (–6.7) 14.7 (–9.6) 15.0 Spanwise ridge EG1150 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 15.0 Spanwise ridge a EG1151 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 15.0 Spanwise ridge a EG1152 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 20.0 Spanwise ridge EG1153 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 15.0 Spanwise ridge, mold EG1154 150 –1.5 20.0 0.81 24.0 (–4.4) 18.4 (–7.6) 15.0 Spanwise ridge EG1155 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 17.5 Spanwise ridge a EG1156 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 17.5 Spanwise ridge a EG1157 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 17.5 Spanwise ridge a EG1158 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 17.5 Spanwise ridge EG1159 150 1.5 20.0 0.81 20.0 (–6.7) 14.7 (–9.6) 15.0 Spanwise ridge, repeat 1151, mold EG1160 175 2.0 30.0 0.50 –5 (–20.6) –12.2 (–24.6) 10.0 Streamwise EG1161 150 2.0 30.0 0.55 –8 (–22.2) –13.3 (–25.2) 10.0 Streamwise EG1162 150 2.0 30.0 0.55 –8 (–22.2) –13.3 (–25.2) 10.0 Streamwise, repeat 1161, mold EG1163 175 5.0 15.0 0.64 28.0 (–2.2) 20.8 (–6.2) 10.0 Horn EG1164 175 5.0 20.0 0.85 28.0 (–2.2) 20.8 (–6.2) 11.25 Horn, repeat 1139, mold a Multiple runs at the same icing conditions were at various heater settings and resulted in varying spanwise ridge ice accretions.

b 5 min at each AoA .

NASA/TP—2016-218348 30 F1 Test Matrices Clean Model With Trip Strips Clean Model TABLE D.5.—CONTINUOUS- AoA SWEEP TABLE D.3.—CONTINUOUS- AoA SWEEP TESTS BY LOT NUMBER TESTS BY LOT NUMBER [Sweep rate: 0.1 deg/s.]

[Sweep rate: 0.1 deg/s.]

M Re × 10 M Re × 10 0.10 0.20–0.21 0.29 0.10 0.20–0.21 0.29 4.5 610 ---- ---- 4.6 392 ---- ----- 8.0–9.0 532 628 ---- 8.0–9.1 325 405 ----- 12.0–12.2 510 576 646 12.0–12.3 308 357 472 a 15.9 ---- 558 ---- a 15.9 ---- 338 ---- a Model pin contact near stall.

a Model pin contact near stall.

TABLE D.6.—FIXED PITCH TESTS BY LOT NUMBER TABLE D.4.—FIXED-PITCH TESTS BY LOT NUMBER AoA , 6 Re × 10 AoA , Re × 10 deg deg –5 0 5 10 15 –5 0 5 10 15 (a) M = 0.10 (a) M = 0.10 4.5 613 615 617 619 621 4.6–4.7 395 418 399 401 403 8.0 535 537 539 541 543 8.1 328 330 332 334 336 12.0–12.2 513 515 517 519 521 12.2–12.3 311 313 315 317 319 (b) M = 0.20–0.21 (b) M = 0.20–0.21 9.0 631 633 635 637 639 9.1 408 410 412 414 ---- 11.9–12.0 579 581 583 585 587 11.9–12.0 372 376 378 380 382 a 15.9–16.0 561 563 565 567 569 15.9 341 343 345 347 ---- (c) M = 0.29 (c) M = 0.28–0.29 12.2–12.3 649 651 653 655 ----- 12.1–12.2 475 477 479 481 ---- a Model pin contact near stall.

NASA/TP—2016-218348 31 Horn Ice, Run EG1164 Streamwise Ice 1, Run EG1162 TABLE D.7.—CONTINUOUS- AoA SWEEP TABLE D.9.—CONTINUOUS- AoA SWEEP TESTS BY LOT NUMBER TESTS BY LOT NUMBER [Sweep rate: 0.1 deg/s.] [Sweep rate: 0.1 deg/s.]

6 6 Re × 10 M Re × 10 M 0.10 0.20–0.21 0.29 0.10 0.20–0.21 0.29 4.5 763 ----- ----- 4.5 861 ----- ----- 8.3–9.0 726 772 ----- 8.5–9.0 816 870 ----- 12.2 701 749 781 12.1–12.2 801 839 879 15.9 ----- 736 ----- 16.0 ----- 825 ----- TABLE D.8.—FIXED PITCH TESTS BY LOT NUMBER TABLE D.10.—FIXED PITCH TESTS BY LOT NUMBER 6 6 Re × 10 AoA , Re × 10 AoA , deg deg –4 0 4 6 8 10 –4 0 4 8 10 12 (a) M = 0.10 (a) M = 0.10 4.5 765 766 767 768 769 770 4.5 863 864 865 866 867 868 8.2–8.3 728 729 731 732 733 734 8.4 818 819 820 821 822 823 11.9–12.1 704 706 708 710 712 714 12.2–12.3 803 804 805 806 807 808 (b) M = 0.20–0.21 (b) M = 0.20–0.21 8.8–9.0 774 775 776 777 778 779 8.9–9.0 872 873 874 875 876 877 12.0–12.2 751 752 753 754 755 756 12.0–12.2 841 842 843 844 845 846 15.6–16.0 738 739 740 741 742 743 15.7–15.9 827 828 829 830 831 832 (c) M = 0.29 (c) M = 0.28–0.29 12.1–12.2 783 784 785 786 787 ----- 12.1–12.2 881 882 883 884 885 ----- NASA/TP—2016-218348 32 Roughness Ice 1, Run EG1126 Spanwise Ridge Ice, Run EG1159 TABLE D.11.—CONTINUOUS- AoA SWEEP TABLE D.13.—CONTINUOUS- AoA SWEEP TESTS BY LOT NUMBER TESTS BY LOT NUMBER [Sweep rate: 0.1 deg/s.] [Sweep rate: 0.1 deg/s.]

6 6 M M Re × 10 Re × 10 0.10–0.11 0.20 0.29 0.10–0.11 0.20 0.29 4.5 985 ----- ------ 4.6 1124 ------ ------ 8.6–8.8 945 994 ------ 8.4–8.7 1079 1135 ------ 12.1 919 970 1003 12.1–12.2 1060 1106 1145 15.9 ----- 954 ------ 16.0 ------ 1090 ------ TABLE D.12.—FIXED PITCH TESTS BY LOT NUMBER TABLE D.14.—FIXED PITCH TESTS BY LOT NUMBER 6 6 AoA , AoA , Re × 10 Re × 10 deg deg –4 0 4 8 10 11 –4 0 2 4 5 (a) M = 0.10–0.11 (a) M = 0.10–0.11 4.6 987 988 989 990 991 992 4.6 1118 1119 1120 1121 1122 8.6–8.7 947 948 949 950 951 952 8.4 1073 1074 1075 1076 1077 12.1–12.2 921 922 923 924 925 926 12.1–12.2 1054 1055 1056 1057 1058 (b) M = 0.20–0.21 (b) M = 0.20–0.21 8.8 996 997 998 999 1000 1001 8.6–8.7 1129 1130 1131 1132 1133 12.1 972 973 974 975 976 977 12.1–12.3 1100 1101 1102 1103 1104 15.9–16.0 956 957 958 959 960 961 15.8–16.0 1084 1085 1086 1087 1088 (c) M = 0.29 (c) M = 0.29 12.1–12.2 1005 1006 1007 1008 1009 ----- 12.0–12.2 1140 1141 1142 1143 ------ NASA/TP—2016-218348 33 Streamwise Ice 2, Run EG1125 Roughness Ice 2, Run EG1134 TABLE D.15.—CONTINUOUS- AoA SWEEP TABLE D.17.—CONTINUOUS- AoA SWEEP TESTS BY LOT NUMBER TESTS BY LOT NUMBER [Sweep rate: 0.1 deg/s.] [Sweep rate: 0.1 deg/s.]

6 6 M M Re × 10 Re × 10 0.10 0.21 0.29 0.10–0.11 0.21 0.29 4.5 1359 ------ ------ 4.6 1482 ------ ------ 8.2–8.9 1220 1290 ------ 8.3–9.0 1429 1494 ------ 12.1–12.2 1338 1253 1301 12.2 1398 1464 1505 16.0 ------ 1232 ------ 15.8 ------ 1441 ------ TABLE D.16.—FIXED PITCH TESTS BY LOT NUMBER TABLE D.18.—FIXED PITCH TESTS BY LOT NUMBER 6 6 AoA , AoA , Re × 10 Re × 10 deg deg –4 0 4 8 10 11 –4 0 4 8 10 12 (a) M = 0.10 (a) M = 0.10–0.11 4.5 1352 1353 1354 1355 1356 1357 4.6 1475 1476 1477 1478 1479 1480 8.2–8.3 1213 1234 1215 1216 1217 1218 8.3–8.4 1421 1423 1424 1425 1426 1427 12.1–12.2 1331 1332 1333 1334 1335 1336 12.1–12.3 1390 1403 1404 1405 1395 1396 (b) M = 0.20–0.21 (b) M = 0.20–0.21 8.9–9.0 1283 1284 1285 1286 1287 1288 9.0 1487 1488 1489 1490 1491 1492 12.1 1246 1247 1248 1249 1250 1251 12.2–12.3 1456 1457 1458 1459 1461 1462 15.9–16.0 1225 1226 1227 1228 1229 1230 15.9–16.0 1434 1435 1436 1437 1438 1439 (c) M = 0.29 (c) M = 0.29 12.2 1295 1296 1297 1298 1299 ------ 12.1–12.2 1499 1500 1501 1502 1503 ------ NASA/TP—2016-218348 34

Appendix E.—Icing Research Tunnel Chord Subscale Model Test Results

Aerodynamic Test of Clean Model Aerodynamic Test of Clean Model NASA/TP—2016-218348 35 Appendix E.—IRT Subscale Model Tests Run ED0711 Run ED0711 NASA/TP—2016-218348 36 Appendix E.—IRT Subscale Model Tests Run ED0712 Run ED0712 NASA/TP—2016-218348 37 Appendix E.—IRT Subscale Model Tests Run ED0713 Run ED0713 NASA/TP—2016-218348 38 Appendix E.—IRT Subscale Model Tests Run ED0714 Run ED0714 NASA/TP—2016-218348 39 Appendix E.—IRT Subscale Model Tests Run ED0715 Run ED0715 NASA/TP—2016-218348 40 Appendix E.—IRT Subscale Model Tests Run ED0716 Run ED0716 NASA/TP—2016-218348 41 Appendix E.—IRT Subscale Model Tests Run ED0717 Run ED0717 NASA/TP—2016-218348 42 Appendix E.—IRT Subscale Model Tests Run ED0718 Run ED0718 NASA/TP—2016-218348 43 Appendix E.—IRT Subscale Model Tests Run ED0719 Run ED0719 NASA/TP—2016-218348 44 Appendix E.—IRT Subscale Model Tests Run ED0720 Run ED0720 NASA/TP—2016-218348 45 Appendix E.—IRT Subscale Model Tests Run ED0721 Run ED0721 NASA/TP—2016-218348 46 Appendix E.—IRT Subscale Model Tests Run ED0722 Run ED0722 NASA/TP—2016-218348 47 Appendix E.—IRT Subscale Model Tests Run ED0723 Run ED0723 NASA/TP—2016-218348 48 Appendix E.—IRT Subscale Model Tests Run ED0724 Run ED0724 NASA/TP—2016-218348 49 Appendix E—IRT Subscale Model Tests Run ED0725 Run ED0725 NASA/TP—2016-218348 50 Appendix E.—IRT Subscale Model Tests Run ED0726 Run ED0726 NASA/TP—2016-218348 51 Appendix E.—IRT Subscale Model Tests Run ED0727 Run ED0727 NASA/TP—2016-218348 52 Appendix E.—IRT Subscale Model Tests Run ED0728 Run ED0728 NASA/TP—2016-218348 53 Appendix E.—IRT Subscale Model Tests Run ED0729 Run ED0729 NASA/TP—2016-218348 54 Appendix E.—IRT Subscale Model Tests Run ED0730 Run ED0730 NASA/TP—2016-218348 55 Appendix E.—IRT Subscale Model Tests Run ED0731 Run ED0731 NASA/TP—2016-218348 56 Appendix E.—IRT Subscale Model Tests Run ED0732 Run ED0732 NASA/TP—2016-218348 57 Appendix E.—IRT Subscale Model Tests Run ED0733 Run ED0733 NASA/TP—2016-218348 58 Appendix E.—IRT Subscale Model Tests Run ED0734 Run ED0734 NASA/TP—2016-218348 59 Appendix E.—IRT Subscale Model Tests Run ED0735 Run ED0735 NASA/TP—2016-218348 60 Appendix E.—IRT Subscale Model Tests Run ED0736 Run ED0736 NASA/TP—2016-218348 61 Appendix E.—IRT Subscale Model Tests Run ED0737 Run ED0737 NASA/TP—2016-218348 62 Appendix E.—IRT Subscale Model Tests Run ED0738 Run ED0738 NASA/TP—2016-218348 63 Appendix E.—IRT Subscale Model Tests Run ED0739 Run ED0739 Appendix E.—IRT Subscale Model Tests NASA/TP—2016-218348 64 Run ED0740 Run ED0740 NASA/TP—2016-218348 65 Appendix E.—IRT Subscale Model Tests Run ED0741 Run ED0741 NASA/TP—2016-218348 66 Appendix E.—IRT Subscale Model Tests Run ED0742 Run ED0742 NASA/TP—2016-218348 67 Appendix E.—IRT Subscale Model Tests Run ED0743 Run ED0743 NASA/TP—2016-218348 68 Appendix E.—IRT Subscale Model Tests Run ED0744 Run ED0744 NASA/TP—2016-218348 69 Appendix E.—IRT Subscale Model Tests Run ED0745 Run ED0745 NASA/TP—2016-218348 70 Appendix E.—IRT Subscale Model Tests Run ED0746 Run ED0746 Appendix E.—IRT Subscale Model Tests NASA/TP—2016-218348 71 Run ED0747 Run ED0747 NASA/TP—2016-218348 72 Appendix E.—IRT Subscale Model Tests Run ED0748 Run ED0748 NASA/TP—2016-218348 73 Appendix E.—IRT Subscale Model Tests Run ED0749 Run ED0749 NASA/TP—2016-218348 74 Appendix E.—IRT Subscale Model Tests Run ED0750 Run ED0750 NASA/TP—2016-218348 75 Appendix E.—IRT Subscale Model Tests Run ED0751 Run ED0751 NASA/TP—2016-218348 76 Appendix E.—IRT Subscale Model Tests Run ED0752 Run ED0752 NASA/TP—2016-218348 77 Appendix E.—IRT Subscale Model Tests Run ED0753 Run ED0753 NASA/TP—2016-218348 78 Appendix E.—IRT Subscale Model Tests Run ED0754 Run ED0754 NASA/TP—2016-218348 79 Appendix E.—IRT Subscale Model Tests Run ED0755 Run ED0755 NASA/TP—2016-218348 80 Appendix E.—IRT Subscale Model Tests Run ED0756 Run ED0756 NASA/TP—2016-218348 81 Appendix E.—IRT Subscale Model Tests Run ED0757 Run ED0757 NASA/TP—2016-218348 82 Appendix E.—IRT Subscale Model Tests Run ED0758 Run ED0758 NASA/TP—2016-218348 83 Appendix E.—IRT Subscale Model Tests Run ED0759 Run ED0759 NASA/TP—2016-218348 84 Appendix E.—IRT Subscale Model Tests Run ED0760 Run ED0760 NASA/TP—2016-218348 85 Appendix E.—IRT Subscale Model Tests Run ED0761 Run ED0761 NASA/TP—2016-218348 86 Appendix E.—IRT Subscale Model Tests Run ED0762 Run ED0762 NASA/TP—2016-218348 87 Appendix E.—IRT Subscale Model Tests Run ED0763 Run ED0763 NASA/TP—2016-218348 88 Appendix E.—IRT Subscale Model Tests Run ED0764 Run ED0764 NASA/TP—2016-218348 89 Appendix E.—IRT Subscale Model Tests Run ED0765 Run ED0765 NASA/TP—2016-218348 90 Appendix E.—IRT Subscale Model Tests Run ED0766 Run ED0766 NASA/TP—2016-218348 91 Appendix E.—IRT Subscale Model Tests Run ED0767 Run ED0767 NASA/TP—2016-218348 92 Appendix E.—IRT Subscale Model Tests Run ED0768 Run ED0768 NASA/TP—2016-218348 93 Appendix E.—IRT Subscale Model Tests Run ED0769 Run ED0769 NASA/TP—2016-218348 94 Appendix E.—IRT Subscale Model Tests Run ED0770 Run ED0770 NASA/TP—2016-218348 95 Appendix E.—IRT Subscale Model Tests Run ED0771 Run ED0771 NASA/TP—2016-218348 96 Appendix E.—IRT Subscale Model Tests Run ED0772 Run ED0772 NASA/TP—2016-218348 97 Appendix E.—IRT Subscale Model Tests Run ED0773 Run ED0773 NASA/TP—2016-218348 98

Appendix F.—Icing Research Tunnel NACA 23012 Full-Scale Model Test Results

Aerodynamic Test of Clean Model Aerodynamic Test of Clean Model NASA/TP—2016-218348 99 Appendix F.—IRT Full-Scale Model Tests Run EG1109 Run EG1109 NASA/TP—2016-218348 100 Appendix F.—IRT Full-Scale Model Tests Run EG1110 Run EG1110 NASA/TP—2016-218348 101 Appendix F.—IRT Full-Scale Model Tests Run EG1111 Run EG1111 NASA/TP—2016-218348 102 Appendix F.—IRT Full-Scale Model Tests Run EG1112 Run EG1112 NASA/TP—2016-218348 103 Appendix F.—IRT Full-Scale Model Tests Run EG1113 Run EG1113 Appendix F.—IRT Full-Scale Model Tests NASA/TP—2016-218348 104 Run EG1114 Run EG1114 NASA/TP—2016-218348 105 Appendix F.—IRT Full-Scale Model Tests Run EG1115 Run EG1115 NASA/TP—2016-218348 106 Appendix F.—IRT Full-Scale Model Tests Run EG1116 Run EG1116 NASA/TP—2016-218348 107 Appendix F.—IRT Full-Scale Model Tests Run EG1117 Run EG1117 NASA/TP—2016-218348 108 Appendix F.—IRT Full-Scale Model Tests Run EG1118 Run EG1118 NASA/TP—2016-218348 109 Appendix F.—IRT Full-Scale Model Tests Run EG1119 Run EG1119 NASA/TP—2016-218348 110 Appendix F.—IRT Full-Scale Model Tests Run EG1120 Run EG1120 NASA/TP—2016-218348 111 Appendix F.—IRT Full-Scale Model Tests Run EG1121 Run EG1121 NASA/TP—2016-218348 112 Appendix F.—IRT Full-Scale Model Tests Run EG1122 Run EG1122 NASA/TP—2016-218348 113 Appendix F.—IRT Full-Scale Model Tests Run EG1123 Run EG1123 NASA/TP—2016-218348 114 Appendix F.—IRT Full-Scale Model Tests Run EG1124 Run EG1124 NASA/TP—2016-218348 115 Appendix F.—IRT Full-Scale Model Tests Run EG1125 Run EG1125 NASA/TP—2016-218348 116 Appendix F.—IRT Full-Scale Model Tests Run EG1126 Run EG1126 NASA/TP—2016-218348 117 Appendix F.—IRT Full-Scale Model Tests Run EG1127 Run EG1127 NASA/TP—2016-218348 118 Appendix F.—IRT Full-Scale Model Tests Run EG1128 Run EG1128 NASA/TP—2016-218348 119 Appendix F.—IRT Full-Scale Model Tests Run EG1129 Run EG1129 Appendix F.—IRT Full-Scale Model Tests NASA/TP—2016-218348 120 Run EG1130 Run EG1130 NASA/TP—2016-218348 121 Appendix F.—IRT Full-Scale Model Tests Run EG1131 Run EG1131 NASA/TP—2016-218348 122 Appendix F.—IRT Full-Scale Model Tests Run EG1132 Run EG1132 NASA/TP—2016-218348 123 Appendix F.—IRT Full-Scale Model Tests Run EG1133 Run EG1133 NASA/TP—2016-218348 124 Appendix F.—IRT Full-Scale Model Tests Run EG1134 Run EG1134 NASA/TP—2016-218348 125 Appendix F.—IRT Full-Scale Model Tests Run EG1135 Run EG1135 NASA/TP—2016-218348 126 Appendix F.—IRT Full-Scale Model Tests Run EG1136 Run EG1136 NASA/TP—2016-218348 127 Appendix F.—IRT Full-Scale Model Tests Run EG1137 Run EG1137 NASA/TP—2016-218348 128 Appendix F.—IRT Full-Scale Model Tests Run EG1138 Run EG1138 NASA/TP—2016-218348 129 Appendix F.—IRT Full-Scale Model Tests Run EG1139 Run EG1139 NASA/TP—2016-218348 130 Appendix F.—IRT Full-Scale Model Tests Run EG1140 Run EG1140 NASA/TP—2016-218348 131 Appendix F.—IRT Full-Scale Model Tests Run EG1141 Run EG1141 NASA/TP—2016-218348 132 Appendix F.—IRT Full-Scale Model Tests Run EG1142 Run EG1142 NASA/TP—2016-218348 133 Appendix F.—IRT Full-Scale Model Tests Run EG1143 Run EG1143 NASA/TP—2016-218348 134 Appendix F.—IRT Full-Scale Model Tests Run EG1144 Run EG1144 NASA/TP—2016-218348 135 Appendix F.—IRT Full-Scale Model Tests Run EG1145 Run EG1145 NASA/TP—2016-218348 136 Appendix F.—IRT Full-Scale Model Tests Run EG1146 Run EG1146 NASA/TP—2016-218348 137 Appendix F.—IRT Full-Scale Model Tests Run EG1147 Run EG1147 NASA/TP—2016-218348 138 Appendix F.—IRT Full-Scale Model Tests Run EG1148 Run EG1148 NASA/TP—2016-218348 139 Appendix F.—IRT Full-Scale Model Tests Run EG1149 Run EG1149 NASA/TP—2016-218348 140 Appendix F.—IRT Full-Scale Model Tests Run EG1150 Run EG1150 NASA/TP—2016-218348 141 Appendix F.—IRT Full-Scale Model Tests Run EG1151 Run EG1151 NASA/TP—2016-218348 142 Appendix F.—IRT Full-Scale Model Tests Run EG1152 Run EG1152 NASA/TP—2016-218348 143 Appendix F.—IRT Full-Scale Model Tests Run EG1153 Run EG1153 NASA/TP—2016-218348 144 Appendix F.—IRT Full-Scale Model Tests Run EG1154 Run EG1154 NASA/TP—2016-218348 145 Appendix F.—IRT Full-Scale Model Tests Run EG1155 Run EG1155 NASA/TP—2016-218348 146 Appendix F.—IRT Full-Scale Model Tests Run EG1156 Run EG1156 NASA/TP—2016-218348 147 Appendix F.—IRT Full-Scale Model Tests Run EG1157 Run EG1157 NASA/TP—2016-218348 148 Appendix F.—IRT Full-Scale Model Tests Run EG1158 Run EG1158 NASA/TP—2016-218348 149 Appendix F.—IRT Full-Scale Model Tests Run EG1159 Run EG1159 NASA/TP—2016-218348 150 Appendix F.—IRT Full-Scale Model Tests Run EG1160 Run EG1160 NASA/TP—2016-218348 151 Appendix F.—IRT Full-Scale Model Tests Run EG1161 Run EG1161 NASA/TP—2016-218348 152 Appendix F.—IRT Full-Scale Model Tests Run EG1162 Run EG1162 NASA/TP—2016-218348 153 Appendix F.—IRT Full-Scale Model Tests Run EG1163 Run EG1163 NASA/TP—2016-218348 154 Appendix F.—IRT Full-Scale Model Tests Run EG1164 Run EG1164 NASA/TP—2016-218348 155

Appendix G.—F1 Subsonic Pressurized Wind Tunnel

NACA 23012 Full-Scale Model Test Results

Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 NASA/TP—2016-218348 157 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 NASA/TP—2016-218348 158 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 NASA/TP—2016-218348 159 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 NASA/TP—2016-218348 160 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 Clean Airfoil: M = 0.10 and Re = 4.6–4.7×10 NASA/TP—2016-218348 161 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 8.1×10 Clean Airfoil: M = 0.10 and Re = 8.1×10 NASA/TP—2016-218348 162 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 8.1×10 Clean Airfoil: M = 0.10 and Re = 8.1×10 NASA/TP—2016-218348 163 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 8.1×10 Clean Airfoil: M = 0.10 and Re = 8.1×10 NASA/TP—2016-218348 164 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 8.1×10 Clean Airfoil: M = 0.10 and Re = 8.1×10 NASA/TP—2016-218348 165 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 8.1×10 Clean Airfoil: M = 0.10 and Re = 8.1×10 NASA/TP—2016-218348 166 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 NASA/TP—2016-218348 167 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 NASA/TP—2016-218348 168 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 NASA/TP—2016-218348 169 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 NASA/TP—2016-218348 170 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 Clean Airfoil: M = 0.10 and Re = 12.2–12.3×10 NASA/TP—2016-218348 171 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 NASA/TP—2016-218348 172 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 NASA/TP—2016-218348 173 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 NASA/TP—2016-218348 174 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 NASA/TP—2016-218348 175 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 9.1×10 NASA/TP—2016-218348 176 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 177 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 178 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 179 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 180 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 181 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 and Re = 15.9×10 Clean Airfoil: M = 0.20 and Re = 15.9×10 NASA/TP—2016-218348 182 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 and Re = 15.9×10 Clean Airfoil: M = 0.20 and Re = 15.9×10 NASA/TP—2016-218348 183 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 and Re = 15.9×10 Clean Airfoil: M = 0.20 and Re = 15.9×10 NASA/TP—2016-218348 184 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 and Re = 15.9×10 Clean Airfoil: M = 0.20 and Re = 15.9×10 NASA/TP—2016-218348 185 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.20 and Re = 15.9×10 Clean Airfoil: M = 0.20 and Re = 15.9×10 NASA/TP—2016-218348 186 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 187 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 188 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 189 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 190 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Clean Airfoil: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 191 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 192 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 193 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 194 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 195 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 196 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 NASA/TP—2016-218348 197 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 NASA/TP—2016-218348 198 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 8×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 NASA/TP—2016-218348 199 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 NASA/TP—2016-218348 200 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 8.0×10 NASA/TP—2016-218348 201 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 NASA/TP—2016-218348 202 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 NASA/TP—2016-218348 203 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 NASA/TP—2016-218348 204 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 NASA/TP—2016-218348 205 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 Clean Airfoil With Trip Tape: M = 0.10 and Re = 12.0–12.2×10 NASA/TP—2016-218348 206 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 NASA/TP—2016-218348 207 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 NASA/TP—2016-218348 208 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 NASA/TP—2016-218348 209 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 NASA/TP—2016-218348 210 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 9.0–9.1×10 NASA/TP—2016-218348 211 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 212 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 213 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 214 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 215 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 11.9–12.0×10 NASA/TP—2016-218348 216 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 217 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 218 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 219 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 220 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Clean Airfoil With Trip Tape: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 221 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2 to 12.3×10 Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 NASA/TP—2016-218348 222 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 NASA/TP—2016-218348 223 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 NASA/TP—2016-218348 224 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 NASA/TP—2016-218348 225 Appendix G.—F1 Full-Scale Model Tests Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 Clean Airfoil With Trip Tape: M = 0.29 and Re = 12.2–12.3×10 NASA/TP—2016-218348 226 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 227 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 228 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 229 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 230 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 231 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 232 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 233 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 234 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 235 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 236 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 NASA/TP—2016-218348 237 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 NASA/TP—2016-218348 238 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 NASA/TP—2016-218348 239 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 NASA/TP—2016-218348 240 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 Horn Ice—Lot EG1164: M = 0.10 and Re = 11.9–12.2×10 NASA/TP—2016-218348 241 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 NASA/TP—2016-218348 242 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 NASA/TP—2016-218348 243 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 NASA/TP—2016-218348 244 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 NASA/TP—2016-218348 245 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 8.8–9.0×10 NASA/TP—2016-218348 246 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 247 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 248 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 249 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 250 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 251 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 NASA/TP—2016-218348 252 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 NASA/TP—2016-218348 253 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 NASA/TP—2016-218348 254 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 NASA/TP—2016-218348 255 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 Horn Ice—Lot EG1164: M = 0.20 to 0.21 and Re = 15.6–16.0×10 NASA/TP—2016-218348 256 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 257 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 258 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 259 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 260 Appendix G.—F1 Full-Scale Model Tests Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 Horn Ice—Lot EG1164: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 261 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 262 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 263 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 264 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 265 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 266 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 NASA/TP—2016-218348 267 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 NASA/TP—2016-218348 268 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 NASA/TP—2016-218348 269 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 NASA/TP—2016-218348 270 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 8.4–8.5×10 NASA/TP—2016-218348 271 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 272 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 273 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 274 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 275 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 Streamwise Ice 1—Lot EG1162: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 276 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 277 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 278 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 279 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 280 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 281 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 282 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 283 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 284 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 285 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 12.0–12.2×10 NASA/TP—2016-218348 286 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 NASA/TP—2016-218348 287 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 NASA/TP—2016-218348 288 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 NASA/TP—2016-218348 289 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 NASA/TP—2016-218348 290 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 Streamwise Ice 1—Lot EG1162: M = 0.20 to 0.21 and Re = 15.7–16.0×10 NASA/TP—2016-218348 291 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 292 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 293 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 294 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 295 Appendix G.—F1 Full-Scale Model Tests Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 Streamwise Ice 1—Lot EG1162: M = 0.28 to 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 296 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 NASA/TP—2016-218348 297 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 NASA/TP—2016-218348 298 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 NASA/TP—2016-218348 299 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 NASA/TP—2016-218348 300 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 Roughness Ice 1—Lot EG1126: M = 0.11 and Re = 4.6×10 NASA/TP—2016-218348 301 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 NASA/TP—2016-218348 302 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 NASA/TP—2016-218348 303 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 NASA/TP—2016-218348 304 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 NASA/TP—2016-218348 305 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 8.6–8.7×10 NASA/TP—2016-218348 306 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 307 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 308 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 309 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 310 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 311 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 NASA/TP—2016-218348 312 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 NASA/TP—2016-218348 313 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 NASA/TP—2016-218348 314 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 NASA/TP—2016-218348 315 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 8.8×10 NASA/TP—2016-218348 316 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 NASA/TP—2016-218348 317 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 NASA/TP—2016-218348 318 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 NASA/TP—2016-218348 319 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 NASA/TP—2016-218348 320 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 12.1×10 NASA/TP—2016-218348 321 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 322 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 323 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 324 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 325 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Roughness Ice 1—Lot EG1126: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 326 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 327 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 328 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 329 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 330 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 1—Lot EG1126: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 331 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 NASA/TP—2016-218348 332 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 NASA/TP—2016-218348 333 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 NASA/TP—2016-218348 334 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 NASA/TP—2016-218348 335 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 4.6×10 NASA/TP—2016-218348 336 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 NASA/TP—2016-218348 337 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 NASA/TP—2016-218348 338 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 NASA/TP—2016-218348 339 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 NASA/TP—2016-218348 340 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 to 0.11 and Re = 8.4–8.5×10 NASA/TP—2016-218348 341 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 342 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 343 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 344 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 345 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ridge Ice—Lot EG1159: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 346 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 NASA/TP—2016-218348 347 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 NASA/TP—2016-218348 348 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 NASA/TP—2016-218348 349 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 NASA/TP—2016-218348 350 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 8.6–8.7×10 NASA/TP—2016-218348 351 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 NASA/TP—2016-218348 352 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 NASA/TP—2016-218348 353 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 NASA/TP—2016-218348 354 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 NASA/TP—2016-218348 355 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 12.1–12.3×10 NASA/TP—2016-218348 356 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 357 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 358 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 359 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 360 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Spanwise Ridge Ice—Lot EG1159: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 361 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 NASA/TP—2016-218348 362 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 NASA/TP—2016-218348 363 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 NASA/TP—2016-218348 364 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 NASA/TP—2016-218348 365 Appendix G.—F1 Full-Scale Model Tests Spanwise Ridg e Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 Spanwise Ridge Ice—Lot EG1159: M = 0.29 and Re = 12.0–12.2×10 NASA/TP—2016-218348 366 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 367 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 368 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 369 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 370 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 4.5×10 NASA/TP—2016-218348 371 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 372 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 373 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 374 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 375 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 8.2–8.3×10 NASA/TP—2016-218348 376 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 377 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 378 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 379 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 380 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.10 and Re = 12.1–12.2×10 NASA/TP—2016-218348 381 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 382 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 383 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 384 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 385 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 8.9–9.0×10 NASA/TP—2016-218348 386 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 NASA/TP—2016-218348 387 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 NASA/TP—2016-218348 388 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 NASA/TP—2016-218348 389 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 NASA/TP—2016-218348 390 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 Spanwise Ice 2—Lot EG1125: M = 0.21 and Re = 12.1×10 NASA/TP—2016-218348 391 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 392 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 393 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 394 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 395 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 Spanwise Ice 2—Lot EG1125: M = 0.20 to 0.21 and Re = 15.9–16.0×10 NASA/TP—2016-218348 396 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 NASA/TP—2016-218348 397 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 NASA/TP—2016-218348 398 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 NASA/TP—2016-218348 399 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 NASA/TP—2016-218348 400 Appendix G.—F1 Full-Scale Model Tests Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 Spanwise Ice 2—Lot EG1125: M = 0.29 and Re = 12.2×10 NASA/TP—2016-218348 401 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 NASA/TP—2016-218348 402 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 NASA/TP—2016-218348 403 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 NASA/TP—2016-218348 404 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 NASA/TP—2016-218348 405 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 Roughness Ice 2—Lot EG1134: M = 0.11 and Re = 4.6–4.7×10 NASA/TP—2016-218348 406 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 NASA/TP—2016-218348 407 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 NASA/TP—2016-218348 408 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 NASA/TP—2016-218348 409 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 NASA/TP—2016-218348 410 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 Roughness Ice 2—Lot EG1134: M = 0.10 to 0.11 and Re = 8.3–8.4×10 NASA/TP—2016-218348 411 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 412 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 413 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 414 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 415 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.10 and Re = 12.1–12.3×10 NASA/TP—2016-218348 416 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 NASA/TP—2016-218348 417 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 NASA/TP—2016-218348 418 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 NASA/TP—2016-218348 419 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 NASA/TP—2016-218348 420 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 9.0×10 NASA/TP—2016-218348 421 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 NASA/TP—2016-218348 422 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 NASA/TP—2016-218348 423 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 NASA/TP—2016-218348 424 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 NASA/TP—2016-218348 425 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 12.2–12.3×10 NASA/TP—2016-218348 426 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 427 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 428 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 429 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 430 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 Roughness Ice 2—Lot EG1134: M = 0.20 to 0.21 and Re = 15.8–16.0×10 NASA/TP—2016-218348 431 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 432 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 433 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 434 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 435 Appendix G.—F1 Full-Scale Model Tests Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 Roughness Ice 2—Lot EG1134: M = 0.29 and Re = 12.1–12.2×10 NASA/TP—2016-218348 436 Glenn Icing Research Tunnel. AIAA‒2001‒0229,

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Monroe R.: Flow Quality Surveys of the NASA Glenn 3. Busch, Greg T.: Ice Accretion Aerodynamic Simulation Icing Research Tunnel (2000 Tests). AIAA‒2001‒ on a Subscale Model. M.S. Thesis, Univ. of Illinois, 0232, 2001.

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Flow Quality Improvements Program for the NASA NASA/TP—2016-218348 437