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'Rolling road' moving ground plane. Part of the UK National Wind Tunnel Facility: MARHy wind Tunnel [41] Operational Diameter 5 m (16 ft) by 2.5 m (8 ft 2 in) Hypersonic/supersonic rarefied wind tunnel. No limit running time. Reynolds number /cm: 26.3 < Re < 7522;Mach number: 0.8 < Mach < 20 France
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.
AEDC Hypervelocity Wind Tunnel 9 is a hypersonic wind tunnel owned by the United States Air Force and operated by National Aerospace Solutions The facility can generate high Mach numbers and high Reynolds for hypersonic ground testing and the validation of computational simulations for the Air Force and Department of Defense.
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.
Since then, China has continued to advance its science and technology and is now home to the world’s most powerful hypersonic wind tunnel, the JF-22, which can simulate the conditions in which a ...
A Chinese aerospace firm has completed the first test flight of a passenger plane that it claims can fly at Mach 4 – more than twice the speed of Concorde.. Beijing-based Space Transportation ...
AEDC operates more than 68 test facilities, including, but not limited to, aerodynamic and propulsion wind tunnels, rocket and turbine engine test cells, environmental chambers, arc heaters, ballistic ranges, sled tracks, centrifuges, and other specialized test units. [2]
The facility was designed to provide ground-based simulations of supersonic and hypersonic flight conditions. The combustion air heater can provide total pressures from 200 psia to 2,800 psia (13.6 atm to 190.5 atm) and a total temperatures from 1,200°R to 4,700°R (667 K to 2,611 K).