A Cryogenic Hypersonic Low-Density Wind Tunnel

  • B. D. Henshall
  • E. M. Brower
Conference paper
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 7)


In the past, hypersonic aerodynamics has been concerned primarily with continuum flow. For ballistic re-entry vehicles, it was established in earlier studies [1] 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.


Mach Number Wind Tunnel Test Section Stream Temperature Stagnation Pressure 
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Copyright information

© Springer Science+Business Media New York 1962

Authors and Affiliations

  • B. D. Henshall
    • 1
  • E. M. Brower
    • 1
  1. 1.AVCO CorporationWilmingtonUSA

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