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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. A wind tunnel is "an apparatus for producing a controlled stream of air for conducting aerodynamic experiments". [1]
Standard models are used in order to verify, by comparison of wind tunnel test results with previously published results, the complete measurement chain in a wind tunnel, including wind tunnel structure, quality of the airstream, model positioning, transducers and force balances, data acquisition system and data reduction software. [2] [3]
AGARD-B is a standard wind tunnel model (calibration model) that is used to verify, by comparison of test results with previously published data, the measurement chain in a wind tunnel. Together with its derivative AGARD-C it belongs to a family [ 1 ] of AGARD standard wind tunnel models.
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)
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AGARD-C standard wind tunnel model on a sting fixture (CAD model) AGARD-C wind tunnel model on a bent sting (CAD model) A hypothetical wind tunnel model on a Z-sting (CAD model) In experimental fluid mechanics, a sting is a test fixture on which models are mounted for testing, e.g. in a wind tunnel. A sting is usually a long shaft attaching to ...
NASA Langley's Hypersonic Facilities Complex, 1969. A hypersonic wind tunnel is designed to generate a hypersonic flow field in the working section, thus simulating the typical flow features of this flow regime - including compression shocks and pronounced boundary layer effects, entropy layer and viscous interaction zones and most importantly high total temperatures of the flow.
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 ...