Silhouette of workman in the 8×6 Foot Wind Tunnel.
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GRC 8×6 and 9×15 Lobby Virtual Tour
The 8×6 SWT provides customers with a facility capable of testing large scale aeropropulsion hardware.
- In a continuous airstream at Mach numbers from 0 to 0.1 and 0.25 to 2.0
- At varying Reynolds Numbers from 3.6 to 4.8×106/ft and altitude conditions (1,000 to 35,000 ft), depending on Mach number
- In either aerodynamic (closed) or propulsion (open) cycle without exhaust scoops
- Employing high accuracy data systems to support steady and transient data acquisition
- Supported by a variety of systems including Schlieren, sheet lasers, GH2 fuel, high-pressure air, and hydraulics
- 1-in. diameter perforations allow for either 3.1 or 6.2 percent porosity variation for test section boundary layer control
Characteristics and Performance
- Test section size: 8-ft high by 6-ft wide by 23.5-ft long
- Mach number range: 0 to 0.1 and 0.25 to 2.0
- Relative altitude: 1,000 to 35,000 ft
- Reynolds Number: 3.6 to 4.8×106/ft
- Stagnation Pressure: 15.3 to 25 psia
- Temperature: 520 to 720°R
- Dynamic Pressure: 200 to 1,340 psf
Tunnel Support Systems
- Combustion Air: 40, 150 and 450-psig
- Service Air: 125 psig
- Combustion Air Heater: 15 pps at up to 750 °F
- Exhaust: 16-in. line at 20 and 26 in of Hg
- High-Pressure Air Storage: 951,000 scf at 2600 psig
- GH2 Fuel System: 1.0 pps at 2200 psig from
- 70000 scf trailers
- Model Cooling
Model Support Systems
- Ceiling Strut Assembly: angle of attack range between
- -5.0 and 15.0°
- Transonic Sting Strut Assembly: Floor mounted with angle of attack range between 0 and 15.0°
- Supersonic Strut: Floor mounted with an angle of attack range between -5 and 20°; axial movement (manual)
- Wall Mount: Typical of halfspan models
- Jet Exit Rig: Ceiling mounted strut with hot gas capabilities for nozzle research
8’x6′ Supersonic Wind Tunnel (8×6) Fact Sheet
GRC Research Facilities
Find out more about the research facilities at NASA’s Glenn Research Center
