Search results
Results from the WOW.Com Content Network
During WWII, Germany developed different designs of large wind tunnels to further their knowledge of aeronautics. For example, the wind tunnel at Peenemünde was a novel wind tunnel design that allowed for high-speed airflow research, but brought several design challenges regarding constructing a high-speed wind tunnel at scale. However, it ...
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.
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)
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. The Reynolds number is varied by changing the density level (pressure in the settling chamber).
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 ...
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 ...
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.
It was the first of many now-famous NACA and NASA wind tunnels. Although this specific wind tunnel was not unique or advanced, it enabled NACA engineers and scientists to develop and test new and advanced concepts in aerodynamics and to improve future wind tunnel design. Atmospheric 5-ft wind tunnel (1920) Variable Density Tunnel (1922)