Document
NASA Ames Research Center
Capabilities of the Unitary Plan Wind Tunnel
Frank Kmak
Chief, Wind Tunnel Division
Ames Research Center
January 11, 2015
ARC Unitary Plan Wind Tunnel
NASA Ames Research Center
Wind Tunnel Division Facilities
High Pressure Air Fluid Mechanics (HPA) Storage Laboratory (FML) Tanks High Pressure Air (HPA) High Pressure Air (HPA) Compressor Compressor C1D C1A & HPA Control Room Unitary Plan Wind Tunnel (UPWT) 12-Ft PWT Model Preparation Rooms (MPR) Balance Calibration Laboratory 12-Ft PWT Mitsubishi Makeup Compressor Air (MUA) Blade Shop Compressor
Reynolds Number Range
9x7-Foot Supersonic Wind Tunnel 11x11-Foot Transonic Wind Tunnel 10.0 !
9.0 !
!
8.0 !
7.0 !
6.0 !
5.0 !
4.0 !
3.0 !
Reynolds Number (Millions per foot) 2.0 !
1.0 !
0.0 !
0.0 ! 0.5 ! 1.0 ! 1.5 ! 2.0 ! 2.5 ! 3.0 !
Mach Number !
11-by 11-Foot Transonic Test Section
• Excellent Flow Quality • Turbulence Reduction System • Excellent optical access • Wall interference correction system • Sting mount and turntable model supports • Complete automation of tunnel and model support operations • Modern control room • Slotted-wall test section (22’) with baffles and 6% porosity • 3-stage compressor and variable camber inlet guide vanes T11-0245/0255 - NASA ERA UHB Powered Semi-span Test OPERATING CHARACTERISTICS OF THE !
NASA AMES RESEARCH CENTER !
11-BY 11-FOOT TRANSONIC WIND TUNNEL !
12.0 !
Stagnation Temperature = 560° R !
Total !
Pressure !
11.0 ! (psfa) !
1900 !
176 MW Power Limit !
1800 !
10.0 ! Test Section !
1700 !
Dynamic Pressure !
1600 !
q (psf) !
1500 ! 4608 !
1400 !
9.0 !
1300 !
4320 !
! 1200 !
Maximum !
Operating !
1100 !
Pressure !
8.0 !
1000 !
4608 psfa !
900 !
3600 !
800 !
7.0 !
700 !
600 !
6.0 !
2880 !
500 !
400 !
5.0 !
300 !
2160 !
4.0 !
200 !
Reynolds Number (Millions per foot) 3.0 !
1440 !
100 !
2.0 !
720 !
1.0 !
432 !
Minimum Operating Pressure 432 psfa !
0.0 !
0.0 ! 0.1 ! 0.2 ! 0.3 ! 0.4 ! 0.5 ! 0.6 ! 0.7 ! 0.8 ! 0.9 ! 1.0 ! 1.1 ! 1.2 ! 1.3 ! 1.4 ! 1.5 !
Mach Number !
Lower limit of PES !
Source: Test 11-0051 IST Revised 2/2015
Sting Mounted Models in 11x11-Foot
Transonic Test Section
Semi-Span Models in 11x11-Foot
Transonic Test Section
PIV in the 11x11-Foot Transonic Test Section
T11-0247 NESC 120-CA CPAS Comprehensive Study of the Flow Around a Simplified Orion Capsule Model • Wind-tunnel testing of Orion showed boundary-layer state on heat shield significantly affected Crew Module aerodynamics • Agreement between CFD and experiments was poor below ~M 0.8 • Study initiated by NASA Engineering and Safety Center (NESC) to reduce uncertainty in Orion wake flow • Comprehensive measurement suite – Particle Image Velocimetry (PIV) – Pressure Sensitive Paint (PSP) – Infrared (IR) thermography to locate transition and separation lines – Unsteady pressures around heat-shield shoulder and in back shell – Boundary-layer measurements at one location on the heat shield – High-speed shadowgraph videos (6,000 frames per second)
11x11-Foot TWT Optical Access
PSP cameras
and lights
IR window
High-speed
PIV camera
IR window
UPWT Production PSP Capability
• PSP Objectives • Provides global pressure distributions for CFD validation • Provides an alternative for surface pressure measurement on thin model surfaces • Provides integrated loads on model surfaces • PSP Deliverables • Preliminary processed data is available in near- time during test • Final data is delivered 4-6 weeks post-test • PSP System • 8 Photometric CoolSnap Cameras • 40 ISSI 400nm LED lamps • 1 Linux cluster containing 9 computers • Custom Steady-State Lifetime PSP Data Processing Suite
• 3-10 second acquisition time T11-0307- NASA AATT
• Automated data acquisition coordinated
SUGAR TRUSS BRACED
with SDS
WING
• Active Collaboration with AEDC
Production Infrared Flow Visualization
Multi-camera infrared data systems provide real-time flow
visualization with no impact on test productivity
• Four megapixel research grade IR cameras.
• No need for tunnel temperature ramps.
• Optical modeling for simulation of views / test planning.
• Laboratory setup to quantify coating IR effectiveness.
• Synchronized, automatic acquisition with in-line image
processing and real-time video feeds.
• Image processing routines adapted from medical
imaging and cockpit display.
• Secure deliver of data products as they are processed.
• Standard Configuration Data Products: • 1 megapixel movie (.avi) per camera recorded throughout the duration of a pitch-pause vector or continuous sweep.
• Series of still images (.tiff) rendered at each pause point.
• Any test parameter computed by the data system (SDS) may be overlaid onto image data real-time.
• IRIG-B timing.
• All image data named and organized based on Run and Sequence number.
9-by 7-Foot Supersonic Test Section
• Complete automation of tunnel and model support systems • Good optical access • Sting mount model support system • Modern control room • Contoured sliding block nozzle • 11-stage compressor T97-0259 – Boeing N+2 Phase II Validation Test OPERATING CHARACTERISTICS OF THE NASA AMES RESEARCH CENTER 9-BY 7-FOOT SUPERSONIC WIND TUNNEL 8.0 Stagnation Temperature = 560° R 7.5 7.0 Test Section 6.5 Dynamic Pressure q (psf) 176 MW Power Limit 6.0 Total 5.5 Pressure (psfa) 5.0 4.5 3600 4.0 3.5 3.0 2.5 Reynolds Number (Millions per foot) 2.0 1.5 1.0 Nozzle Block Operating Range is 0.5 Minimum Operating Pressure between 1414 and 2475 psfa is 643 psfa (4.4 psia) 0.0 1.4 1.5 1.6 1.7 1.8 1.9 2.0 2.1 2.2 2.3 2.4 2.5 2.6 2.7 Mach Number Source: Test 97-0065 IST 12/2001
Models in 9x7-Foot Supersonic Test Section
Production High-Speed Shadowgraph/Schlieren
Dual shadowgraph systems provide simultaneous low-speed and high-
speed image acquisition
• State-of-the-art high-speed cameras.
• High-powered pulsed LED light sources.
• Automatic acquisition with in-line image processing and real-time video feeds.
• Secure deliver of data products as they are processed.
Standard Configuration Data Products : •Low-Speed: • ~4 megapixel 20 FPS movie (.avi) recorded throughout the duration of a pitch-pause vector or continuous sweep.
• Series of high-resolution still images (.tiff) rendered at each pause point.
•High-Speed: • ~1 megapixel movie (.avi) ~50,000 FPS typical recorded at each point in pitch-pause vector.
• Mean and variance still images (.tiff) computed and rendered at each pause point.
• Any test parameter computed by the data system (SDS) may be overlaid onto image data real-time.
• IRIG-B timing.
• All image data named and organized based on Run and Sequence number.
9x7-Foot SWT Control Room
Operations Area
Operations Area
Customer Area
Facility Control Area
Steady-State Standard Data System (SDS)
SDS is a multi-tasking, multi-user steady- state data system: • Flexible, robust, distributed data platform implemented on open systems architecture.
• Real-time processing, data recording, numerical and graphical displays.
• Concurrent data acquisition & re-compute capabilities.
• User definable displays.
• On-line diagnostic tools for trouble shooting and data quality checks.
• Interfaces with facility control system, customer analysis computers, test dependent data systems, and model controls.
• Secure (isolated) network.
• Expandable to match test specific requirements.
• Supports multiple 6-component balances (5 standard).
• Support up to 2048 static pressure measurements.
• 48 channels of general purpose strain gage measurements.
• Supports RTD, thermocouples, & thermistor temperature measurements • Measures tunnel conditions and test article attitude.
• Optional real-time wall corrections (up to Mach 0.9).
Dynamic Data System (DDS)
The Dynamic Data System (DDS) provides high speed simultaneous acquisition and analysis of fluctuating pressures, acoustics, vibrations, buffet, and other dynamic signals.
Functions and Features • Real-time graphical display in time and frequency domain.
• Concurrent signal monitoring and recording.
• Simultaneous Signal Sampling on all channels.
o 1kS/sec – 204.8kS/sec (DC – 80KHz) • Expandable PXI based architecture: o 300+ channel capability.
o 24 Bit Delta-sigma Analog to Digital Converter o Fully anti-aliased 32 f – 128f oversample rate s s o ±0.316 Vpk to ±42 Vpk input Ranges o AC/DC coupling (AC cutoff 3dB point: 3.4Hz) o Built-in IEPE signal conditioning (4 & 10 mA) • Interfaced with Standard Data System.
o Dynamic data linked to tunnel conditions & point ID.
o Supports automated data acquisition.
• Near Time Signal Processing: o Time domain statistics (Min, Mean, Max, RMS, nSamples, etc.)
o Frequency domain results (PSD’s, Third Octave, ect.)
• Custom fixed gain (50x) pre-amplifier/line-drivers for Kulite® style transducers.
UPWT Model Support Systems
• Sting Model Support System
• Knuckle-Sleeve Device
• 15 cone and changeable
adaptors
• Kick-Sting for Increased
Angle of Attack
• Roll capability
• Data acquisition modes
• Move-pause mode
• Continuous pitch, yaw or
roll mode
• Hybrid mode
AIM-9 using roll mechanism
• Turntable model support
and kick sting
systems in 11’ by 11’
Additional UPWT Systems
• Precision Instrumentation • QA-2000 Angle sensors • Flow Reference System • DTC ESP surface pressure scanners • Flow Visualization • Pressure Sensitive Paint • High-Speed Schlieren • IR Thermography • Particle Image Velocimetry • Oil flows • Mini-tufts • Laser Vapor Screen • Balance Alarm System (BLAMS)
F-18 with pressure sensitive paint
• Video Systems
High Pressure Air (HPA)
• Typical uses of High Pressure Air • Turbine propulsion simulators • Ejector systems • Plume simulations • Air storage capacity of 7.8 million SCF at 3000 psig • HPA Capabilities • Computer controlled mass flow, pressure and temperature • Two 3,000 psia lines delivered at up to 80 lbm/sec.
• 1 MW heater capable of heating o air to 400 F
T97-0186 - CEV 51AS ORION Launch Abort Test
Flow Quality and Calibration
M=0.80, Post-Mod M=0.80, Post-Mod M=0.95, Post-Mod M=0.95, Post-Mod M=0.80, Pre-Mod M=0.80, Pre-Mod 0.50 0.50
• 11x11-Foot TWT Calibration
0.25 0.25 • Static Pipe
• Flow Uniformity Survey
0.00 0.00
• Turbulence and Acoustics
-0.25 -0.25
Survey (AIAA 2000-2681)
Probe Height, z/H, (H = 11 ft) Probe Height, z/H, (H = 11 ft) -0.50 -0.50
• LB-435 Calibration Model
-0.50 -0.25 0.00 0.25 0.50 -0.50 -0.25 0.00 0.25 0.50 CROSSFLOW, (deg) UPFLOW, (deg)
• 9x7-Foot SWT Calibration
0.6 2000, 11' TWT, Slots Normal Post-Mod, Slots Normal 2001, 11' TWT, Slots Normal Post-Mod, Slots Taped 2001, 11' TWT, Partially Taped Slots
• Flow Survey
0.5 Pre-Mod, Slots Normal 1972, 11' TWT, AIAA 72-1004 0.4
• Acoustics Measurements
1.5% CP'rms= 0.3 p'rms/q 1.0% 0.2 0.5% Streamwise Turbulence, % 0.1 0.0% 0.2 0.4 0.6 0.8 1 0 0.5 1 1.5 Mach Mach
NASA Ames UPWT
• Ames UPWT has an outstanding history of
serving the aerospace community
• Ames UPWT offers high Reynolds number
testing over a broad range of Mach numbers
• Our modernized tunnels are extremely capable,