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ARC UPWT Multimedia Gallery

Wind Tunnel Contacts

Aerial view of wind tunnels at NASA Ames. If you would like to do business with the Unitary Plan Wind Tunnel Division at Ames, please visit our contact page.

ARC UPWT Multimedia Gallery

Photographer- Roger Brimmer Date- 06_22_89 Aerial view of Unitary Plan Wind Tunnel complex with NASA insignia. Aerial View of the Unitary Plan Wind Tunnel at NASA Ames
Aerial view of Unitary Plan Wind Tunnel complex with NASA insignia. Image credit: Photographer- Roger Brimmer 06-22-89
 


120-CA Orion Smooth Command Module Model 8.08% Scale
To obtain surface static and unsteady pressures, skin-friction, and flow visualization data to understand the downstream wake structure and to calibrate computational fluid dynamics (CFD) results.
 


120-CA Orion Smooth Command Module Model 8.08% Scale
To obtain surface static and unsteady pressures, skin-friction, and flow visualization data to understand the downstream wake structure and to calibrate computational fluid dynamics (CFD) results.
 


120-CA Orion Smooth Command Module Model 8.08% Scale
To obtain surface static and unsteady pressures, skin-friction, and flow visualization data to understand the downstream wake structure and to calibrate computational fluid dynamics (CFD) results.
 


120-CA Orion Smooth Command Module 8.08% Scale with a Particle Image Velocimetry Plane
To obtain surface static and unsteady pressures, skin-friction, and flow visualization data to understand the downstream wake structure and to calibrate computational fluid dynamics (CFD) results.
 


Model of ISRP ERA UHB Semi-Span in 11-by 11-ft Transonic Wind Tunnel test section. Ultra-High Bypass (UHB) Semi-Span Model
The model is the latest design that uses a new technique, simultaneously optimizing the wing and nacelle for minimum drag in the Unitary Plan Wind Tunnel 11-by 11-foot test section.
 


Model of ISRP ERA UHB Semi-Span in 11-by 11-ft Transonic Wind Tunnel test section. Ultra-High Bypass (UHB) Semi-Span Model in the Unitary Plan Wind Tunnel 11-by 11-foot Test Section
The model is the latest design that uses a new technique, simultaneously optimizing the wing and nacelle for minimum drag in the Unitary Plan Wind Tunnel 11-by 11-foot test section.
 


Model of CEV 80 in wind tunnel. 6% Orion Launch Abort Vehicle (LAV) Model
Test provided measurements of the aeroacoustics of the Orion Launch Abort Vehicle (LAV) configuration. Hot helium was used to simulate abort plumes through scaled Abort Motor nozzles.
 


Common Research Model in wind tunnel Common Research Wind Tunnel Model
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Common Research Model in wind tunnel Common Research Wind Tunnel Model
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Common Research Model in wind tunnel Common Research Wind Tunnel Model
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Common Research Model in Wind Tunnel Common Research Wind Tunnel Model
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Common Research Model in Wind Tunnel Common Research Wind Tunnel Model
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Common Research Model in wind tunnel Common Research Wind Tunnel Model
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Common Research Model in wind tunnel Common Research Wind Tunnel Model with a Particle Image Velocimetry Plane
To obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


Group photo of Common Research team. Common Research Model Test Crew
Obtain aerodynamic and flow visualization data on a generic transport model to assess the performance of computational fluid dynamics (CFD) codes used throughout the aerospace community.
 


2.8% model of CLV reentry in 9-by 7-foot wind tunnel. 2.8% Ares 1 Acoustic Reentry Wind Tunnel Model
Test to determine fluctuating pressure environments from a 2.8% scale Ares I first stage configuration to verify and update reentry aero acoustics environments.
 


2.8% model of CLV re-entry in wind tunnel. 2.8% Ares I Acoustic Reentry Wind Tunnel Model
Test to determine fluctuating pressure environments from a 2.8% scale Ares I first stage configuration to verify and update reentry aero acoustics environments.
 


Model of FAVOR Check Standard in wind tunnel Facility Aerodynamics Validations and Operations Research Model
Cooperative wind tunnel tests to provide engineering insight into facility processes, data reduction, flow quality and a comparative data assessment.
 


Group photo of the FAVOR Check Standard team. Facility Aerodynamics Validations and Operations Research Model Test Crew
Cooperative wind tunnel tests to provide engineering insight into facility processes, data reduction, flow quality and a comparative data assessment.
 


Model of CEV/LAS 51 Aero Acoustics in wind tunnel. 6% Crew Exploration Vehicle/ Launch Abort Vehicle and Encapsulated Service Module
Test to obtain acoustic data on jet interactions of plume simulations with separation aerodynamic effects for selected specific conditions.
 


Model of CEV/LAS 51 Aero Acoustics in wind tunnel. 6% Crew Exploration Vehicle/ Launch Abort Vehicle and Encapsulated Service Module
Test to obtain acoustic data on jet interactions of plume simulations with separation aerodynamic effects for selected specific conditions.
 


Model of UHB TPS SS in 11-by 11-ft transonic wind tunnel at NASA Ames. Ultra High Bypass (UHB) Nacelle Semi Span
Force, moment, and pressure data measurements of the aerodynamic effects on the inboard underside of the wing near the nacelle and pylon for an Ultra High Bypass (UHB) nacelle.
 


Model of shuttle in wind tunnel 3% Space Shuttle Aero Acoustics Wind Tunnel Model
3% space shuttle launch configuration; super light weight (SLWT) external tank with protuberances, orbiter, and RSRB’s.
 


Model of shuttle in wind tunnel. 3% Space Shuttle Aero Acoustics Wind Tunnel Model
3% space shuttle launch configuration; super light weight (SLWT) external tank with protuberances, orbiter, and RSRB’s.
 


Model of CEV/LAS 75 in wind tunnel. 5% Scale Model of the Crew Exploration Vehicle (CEV) Alternate Launch Abort System (ALAS)
To test force, moment, and pressure data measurements of the jet interference effects on the crew exploration vehicle (CEV) alternate launch abort system (ALAS).
 


Model of CEV/LAS 75 in wind tunnel. 5% Scale Model of the Crew Exploration Vehicle (CEV) Alternate Launch Abort System (ALAS)
To test force, moment, and pressure data measurements of the jet interference effects on the crew exploration vehicle (CEV) alternate launch abort system (ALAS).
 


acd04_0177_001.jpgModel of F-18
A model of F-18 is tested in the NASA Ames 11-by 11-foot transonic wind tunnel.
Image credit: NASA Ames Research Center
 


acd04_0177_002.jpgModel of F-18
A model of F-18 is tested in the NASA Ames 11-by 11-foot transonic wind tunnel.
Image credit: NASA Ames Research Center
 


Model of CEV 25 in 9x7 Wind Tunnel 3% Crew Exploration Vehicle (CEV) Command Module and Launch Abort Tower
Test to investigate aerodynamic proximity and jettison motor plume interaction effects on the separation of the crew module from the launch abort tower during an abort from the Ares launch vehicle.
 


Model of CEV-26 test in 9-by 7-foot Wind Tunnel at NASA Ames. Model of Modified 6% Crew Exploration Vehicle (CEV) Calibration Rig
Wind tunnel test to calibrate the flow-around balance model assembly for momentum corrections.

 


CEV 26 model in 9x7 wind tunnel Modified 6% Crew Exploration Vehicle (CEV) Alternate Launch Abort System (ALAS) Configuration
Model of Crew Exploration Vehicle (CEV) with pressure sensitive paint (PSP) to obtain data on jet interactions of plume effects in conjunction with separation aerodynamics effects.
 


Model of TBC-1 in 9x7 Wind Tunnel 0.65% Scale Quiet Experimental Validation Concept (QEVC) Performance Model
Low boom passenger airline concept to obtain force and pressure measurements and calibrate computational fluid dynamics (CFD) tools estimates.
 


Model of TBC-1 in 9x7 Wind Tunnel 1.79% Scale Quiet Experimental Validation Concept (QEVC) Boom 1 Model
Low boom passenger airline concept to obtain force and pressure measurements and calibrate computational fluid dynamics (CFD) tools estimates.
 


Model of LM1 in 9x7 Wind Tunnel Ames Low Boom Wing Tail Model
Model in the Unitary Plan Wind Tunnel 9-by 7-foot test section. Test to refine sonic boom test techniques and measure sonic boom signatures of various supersonic aircraft designs.
 

 

Page Last Updated: February 13th, 2014
Page Editor: Kimberly Aldenbrook