| Facilities |
Improvements |
| 0.3 M Transonic Cryogenic Tunnel |
- New facility control system
- New data acquisition system
|
| 14 X 22 Foot Subsonic Tunnel |
- Four new anti-turbulence screens
- New facility control system
- New data acquisition system
- Electronically driven, low profile model support cart
- New fan motor with increased capability
|
| Jet Exit Test Facility |
- Added a second independently controlled air system
- Improved controls for low-volume flows
|
| Low Turbulence Pressure Tunnel |
- New wake rake system
- Significantly reduced data acquisition time
|
| National Transonic Facility |
- Increased Air Operational Capability
- Improved Data Quality
- Improved Productivity and Efficiency
- Reduced Tunnel Dynamics
|
| Unitary Plan Wind Tunnel |
- New facility control system
- Improved productivity and efficiency
- Advanced modern design of experiments testing methodology
|
| 15-Inch Mach 6 High Temperature Tunnel |
- Improved flow quality via new settling chamber
- Improved flow condition stability with new high pressure air supply system
- Enhanced optical access for advance non-intrusive test technique development
|
| 20-Inch Mach 6 CF4 Tunnel |
- Enhanced productivity with new CF4 gas reclamation system
- Greater flow condition stability with new heater installation
|
| 20-Inch Mach 6 Tunnel |
- Improved flow quality via new settling chamber
- New, high accuracy model attitude control system
- Enhanced productivity through vacuum system improvements
|
| 31-Inch Mach 10 Tunnel |
- Enhanced optical access for advanced non-intrusive test techniques
- Fully automated temperature control for greater flow condition stability
- Improved productivity and efficiency via installation of new vacuum system components
|
| 12-Foot Low-Speed Tunnel |
- Automated tunnel control system
|
| 20-Foot Vertical Spin Tunnel |
- Fully automated rotary balance testing process
- Mechanical upgrades enable greater testing efficiency and greater flexibility
|
| 20-Inch Supersonic Wind Tunnel |
- New testing capability (2-D airfoils at subsonic extra-planetary conditions)
- New model pitch and yaw system
- New second minimum
- New low pressure drop exhaust line
|
| Supersonic Low Disturbance Tunnel |
- Probe traverse mechanism (in progress)
|
| 8 Ft High Temperature Tunnel |
- Modified heater for improved flow uniformity
- Replaced/expanded high-pressure air storage
-
|
| Arc-Heated Scramjet Test Facility |
- Upgraded PLC-based control system
- Upgraded, versatile model fueling system
- New, high-flow-quality, 2-D Mach 6 facility nozzle
|
| Combustion-Heated Scramjet Test Facility |
- 6-component force balance
- Improved electronic scanning pressure system
- Improved facility diffuser system
|
| Direct Connect Supersonic Combustion Test Facility |
- Improved facility productivity and efficiency
- Available coherent anti-Stokes Raman spectroscopy system (CARS)
|
| Transonic Dynamics Tunnel |
- Increased productivity during heavy gas operations
- Added oscillating model-support system
- Fully automated controls (FY 02)
- Added approximately 7,000 square feet of model preparation area
|
