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Evaporative Film Cooling of Blunt Bodies in Hypersonic Flow and its Application to Re-entry Vehicles

  • Rudolf Hermann
Conference paper

Abstract

Evaporative film cooling on blunt nose models has been investigated in a 12″ × 12″ hypersonic blowdown wind tunnel at Mach number 7 with stagnation temperatures up to 2500 °R. Water as coolant was supplied continuously through orifices located near the stagnation point of a hemisphere-cylinder body (3 inch diameter) and a blunt cone with 10° half angle (base diameter 5.5 inches) forming an evaporating water film covering the body. This results in nearly uniform wall temperatures about 30 °R below the local boiling temperature of the water.

Keywords

Mach Number Wind Tunnel Liquid Film Stagnation Point Film Cool 
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References

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    R. Hermann, H. Leitinger and W. L. Melnik, University of Minnesota, Ros. Aero. Lab. Res. Rep. 127 (March 1955) or WADC Tech. Note 55–507.Google Scholar
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Copyright information

© Springer-Verlag Wien 1961

Authors and Affiliations

  • Rudolf Hermann
    • 1
  1. 1.Rosemount Aeronautical LaboratoriesUniversity of MinnesotaMinneapolisUSA

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