A Cryogenic Hypersonic Low-Density Wind Tunnel
In the past, hypersonic aerodynamics has been concerned primarily with continuum flow. For ballistic re-entry vehicles, it was established in earlier studies  that most of the problems which tend to define the vehicle occur at altitudes below 200,000 ft, where the flow is substantially a continuum one. However, lifting re-entry from satellite orbits and any type of space re-entry may give rise to significant aerodynamic problems at altitudes between 200,000 and 500,000 ft. Although the forces are low, they act over relatively long periods of time and may have a lasting effect on the motions of the vehicle and, consequently, its design. Perhaps even more important is the necessity of knowing and understanding the ionized wake characteristics for low radar cross-section vehicles.
KeywordsMach Number Wind Tunnel Test Section Stream Temperature Stagnation Pressure
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