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Therefore, hypersonic boundary layers are high temperature regions due to the viscous dissipation of the flow's kinetic energy. Another region of high temperature flow is the shock layer behind the strong bow shock wave. In the case of the shock layer, the flow's velocity decreases discontinuously as it passes through the shock wave. This ...
Chemically reacting flow can also cause corrosion of the vehicle's skin, with free-atomic oxygen featuring in very high-speed flows. Hypersonic designs are often forced into blunt configurations because of the aerodynamic heating rising with a reduced radius of curvature. — 53T6 (Mach 17) HTV 2 (Mach 20) Agni-V (Mach 24) DF-41 (Mach 25 ...
The HEAT-H2 Test Unit is an arc-heated aerothermal tunnel providing high-enthalpy flow at high Mach numbers and dynamic pressures simulating hypersonic flight at pressure altitudes up to 120 atm. H2 utilitzes an N-4 Huels-type arc heater to generate high-temperature, high-pressure air for expansion through a hypersonic nozzle into the evacuated test cell.
Tunnel B is a 50-inch, closed-circuit hypersonic tunnel with continuous-flow capability with a Mach number capability of 6 and 8. Provided with air heated to a maximum of 900 degrees Fahrenheit with natural gas-fired heaters. Tunnel B is also primarily explores aerodynamic design.
Plasma has been introduced to hypersonic flow control. [30] [31] Firstly, plasma could be much easier generated for hypersonic vehicle at high altitude with quite low atmospheric pressure and high surface temperature. Secondly, the classical aerodynamic surface has little actuation for the case.
NASA Langley Hypersonic 20 Inch Mach 6 Tetrafluoromethane [62] Demolished in 2016 [63] Diameter 508 mm (20 in) Hypersonic United States NASA Langley Hypersonic 31 Inch Mach 10 Air [61] Diameter 787 mm (31 in) Hypersonic United States NASA Langley Hypersonic Propulsion Integration 15 Inch Mach 6 High-Temperature Tunnel [64] Diameter 381 mm (15 in)
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 aeronautics, expansion and shock tunnels are aerodynamic testing facilities with a specific interest in high speeds and high temperature testing. Shock tunnels use steady flow nozzle expansion whereas expansion tunnels use unsteady expansion with higher enthalpy, or thermal energy. In both cases the gases are compressed and heated until the ...
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