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Unitary Plan Wind Tunnel 11-by 11-foot Transonic Test Section

Unitary Plan Wind Tunnel 9-by 7-foot Supersonic Test Section

Test Planning Information

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ARC UPWT Multimedia Gallery

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
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.
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.
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.
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.
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.
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.
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 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 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 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 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 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 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 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.
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% 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% 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.
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.
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.
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.
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.
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.
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.
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.
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).
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).
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 Modified 6% Crew Exploration Vehicle (CEV) Calibration Rig

Wind tunnel test to calibrate the flow-around balance model assembly for momentum corrections.
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.
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.
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.
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.