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Free-jet NASA Glenn Engine Components Research Lab [53] United States NASA Glenn Hypersonic Test Facility [54] Hypersonic United States NASA Glenn Icing Research Tunnel [51] 3 m × 2 m × 6 m (9 ft × 6 ft × 20 ft) Subsonic Icing United States NASA Glenn Propulsion Systems Laboratory [55] Active Diameter 7 m (24 ft) by 12 m (38 ft) long
The power required to run a supersonic wind tunnel is enormous, of the order of 50 MW per square meter of test section cross-sectional area. For this reason most wind tunnels operate intermittently using energy stored in high-pressure tanks.
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A sample wind tunnel layout showing some typical features including a test section and control room, a machine for pumping air continuously through ducting, and a nozzle for setting the test airspeed.
16S is a supersonic wind tunnel that can be configured for Mach numbers from 1.5 to 4.750. The test section is also 16-foot-square and 40-foot long. The facility can simulate unit Reynolds numbers from approximately 0.1 to 2.4 million per foot or altitude conditions from 43,000 to 154,000 feet.