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Large Low Speed Wind Tunnel 2.1 m (6 ft 11 in) by 1.5 m (4 ft 11 in) Low Turbulence Wind Tunnel 0.8 m (2 ft 7 in) by 0.6 m (2 ft 0 in) Open Jet Wind Tunnel 1.1 m (3 ft 7 in) diameter United Kingdom University of British Columbia Boundary Layer Wind Tunnel [90] 2.5 m × 1.6 m × 23.6 m (8 ft 2 in × 5 ft 3 in × 77 ft 5 in)
Wind tunnel test sections range in size from less than a foot across, to over 100 feet (30 m), and with air speeds from a light breeze to hypersonic. The earliest wind tunnels were invented towards the end of the 19th century, in the early days of aeronautical research, as part of the effort to develop heavier-than-air flying machines.
An actual model is built to a size suitable for the size of a specific wind tunnel test section, in particular taking care that the frontal blockage of the model (the ratio of the model cross-section area to wind tunnel test section area) is kept well below 1% (except for wall-interference research where the models may be larger).
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Portion of the Unitary Plan Wind Tunnel in 2014. Construction of this facility began in 1950-1951 and continued until 1955. Because no one wind tunnel could meet all the demands for additional research facilities simulating the entire range of aircraft and missile flight, NACA chose to build the Ames tunnel with three separate test sections drawing power from a common centralized power plant.
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. To mitigate this, perforated or slotted walls are used to ...
The Full-Scale Tunnel [4] (abbreviated FST, also known as the 30-by 60-Foot Tunnel [5]) was a wind tunnel at NASA's Langley Research Center. It was a National Historic Landmark . In 1929, National Advisory Committee for Aeronautics began construction of the world's first full-scale wind tunnel, where high-performance airplane would be tested.
Initially intended for the supersonic wind tunnels, the AGARD-B configuration has since been tested in many wind tunnels at a wide range of Mach numbers, from low subsonic (Mach 0.1), through transonic (Mach 0.7 to 1.4) to hypersonic (up to Mach 8 and above). Therefore, a considerable database of test results is available.