9X15 low-speed wind tunnel nasa glenn research center gas 85 octane

The 9- by 15-Foot Low-Speed Wind Tunnel (9×15) is the most utilized low-speed propulsion acoustic facility in the world. It is the only national facility that can simulate takeoff, approach, and landing in a continuous subsonic environment. Facility Overview Honeywell Predictive Tool Development (PTD) Test in the 9- by 15-Foot Low-Speed Wind Tunnel (9×15).

The 9×15 is a significant asset to the nation and the aero-propulsion community because of its unique ability to test large-scale hardware in a continuous subsonic air stream. With the ever-increasing demand for reducing aircraft noise, the importance of the 9×15 is greater than ever. Offering state-of-the-art acoustic capabilities, the facility is a vital part of the nation’s aeronautics research plans. Programs supported in this facility include a variety of commercial aircraft propulsion systems: the High Speed Civil Transport (HSCT), Advanced Tactical Fighter (ATF), Joint Strike Fighter (JSF) and other military short takeoff and vertical landing (STOVL) aircraft applications.

Built in 1968, the test section of the 9×15 is 9 ft high by 15 ft wide and 33 ft long. Providing airspeeds from 0 to 165 mph, this facility has unique and nationally recognized capabilities to evaluate aerodynamic performance and acoustic characteristics of nozzles, inlets and propellers. General Electric Open Rotor Historic Baseline Blade Assembly Test Hardware in the 9- by 15-Foot Low-Speed Wind Tunnel (9×15).

The facility is acoustically treated and equipped with microphones linked to a dynamic data system. A series of drive rig systems are available to power engine fan models for performance and acoustic testing. A unique “rotor alone nacelle” test capability allows isolation of “fan alone noise” by elimination of outlet guide vanes.

The 9×15, housed in the return leg of the 8- by 6-Foot Supersonic Wind Tunnel (8×6), provides a unique facility for testing large-scale hardware in a continuous subsonic air stream. The test section is 9 ft high by 15 ft wide by 33 ft. long and provides airspeeds from 0 to 165 mph. The facility is used to evaluate aerodynamic performance and acoustic characteristics of nozzles. Name:

The 9×15’s electronically scanned pressure system consists of numerous 32 or 64 port miniaturized pressure scanner modules. Multiple measurement ranges are available to accommodate various needs. These can be located outside of the test chamber or within the test article. Each module has a check pressure to ensure correct performance. In-situ calibration performed via high accuracy standards.

NASA’s Glenn Research Center uses Collect Observe Broadcast Record and Analyze (COBRA) for its standardized low-speed (under 1000 samples per second per channel) data system. The system uses commercial off-the-shelf (COTS) hardware and operating systems coupled with specialized data acquisition and application hardware and software modules. It has a flexible and scalable design that utilizes a distributed network architecture approach. This design allows the attachment of measurement devices from a wide range of vendors. This approach allows the system to evolve over time, permits the latest technology to be used that meets Glenn’s measurement, and provides the environment for the best measurement methods to be applied.

NASA’s Glenn Research Center provides ground test facilities to industry, government, and academia. If you are considering testing in one of our facilities or would like further information about a specific facility or capability, please let us know.