Search results
Results from the WOW.Com Content Network
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.
In 1967, Congress granted approval for the construction of Tunnel 9. The facility became operational in 1976 and has since been providing aerodynamic simulation in critical altitude regimes associated with strategic offensive missile systems, advanced defensive interceptor systems, and hypersonic vehicle technologies.
The facility consists of three Hypersonic wind tunnels: Tunnel A, B, and C. The wind tunnels can be run for several hours at a time thanks to a 92,500 horsepower air compressor plant system. [ 1 ] The test unit is owned by the United States Air Force and operated by National Aerospace Solutions .
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 ...
Part of the UK National Wind Tunnel Facility: CRIACIV Boundary Layer Wind Tunnel - University of Florence [25] Operational 2.44 m × 1.6 m × 10 m (8 ft 0 in × 5 ft 3 in × 32 ft 10 in) Building, bridges, general purpose Italy Closed circuit wind tunnel, T-shaped diffuser, one atmospheric test section (max speed 31 m/s [100 ft/s]).
HYFLEX (Hypersonic Flight Experiment) which was a re-entry demonstrator prototype vehicle of JAXA was tested in this facility. Another speciality of this tunnel is 3 pistons of different masses can be used. [9]
Successful test launch of the Common-Hypersonic Glide Body (C-HGB) in March 2020 from Kauai, Hawaii. Both the Navy and Army plan to deploy hypersonic weapons based on C-HGB.
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).