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A wind tunnel is "an apparatus for producing a controlled stream of air for conducting aerodynamic experiments". [1] The experiment is conducted in the test section of the wind tunnel and a complete tunnel configuration includes air ducting to and from the test section and a device for keeping the air in motion, such as a fan.
Low Speed Wind Tunnel 1.15 m (3 ft 9 in) by 0.95 m (3 ft 1 in) Flow Visualisation Wind Tunnel 0.90 m (2 ft 11 in) by 0.90 m (2 ft 11 in) United Kingdom University of Manchester [17] Operational Hypersonic wind tunnel 6 in (150 mm) diameter Trisonic wind tunnel 0.15 m (5.9 in) by 0.3 m (1 ft 0 in)
Here, Mach 4 flow over a pitot probe is observed by schlieren optics in the Penn State Supersonic Wind Tunnel. The flow direction is left-to-right. A supersonic wind tunnel is a wind tunnel that produces supersonic speeds (1.2<M<5) The Mach number and flow are determined by the nozzle geometry.
Results of wind tunnel tests of these models are generally published in the form of nondimensional aerodynamic coefficients (thus being made independent of model size) and made available to the wind-tunnel community, often in review reports containing inter-facility comparisons of data, [5] [8] [9] [10] discussing observed scatter of results ...
Transonic wind tunnels, between Mach 0.75 and Mach 1.2 (920 and 1,500 km/h; 570 and 910 mph; 260 and 410 m/s), are designed on similar principles as subsonic tunnels but present additional challenges, primarily due to the reflection of shock waves from the walls of the test section.
The El Segundo Trisonic Wind Tunnel or North American Trisonic Wind Tunnel (NATWT) was a wind tunnel that was located in El Segundo, California. [8] It was built by North American Aviation in the 1950s. The tunnel had a maximum testing speed of Mach 3.5. The NATWT was a blow-down type tunnel.