Heat-Transfer Tests of Two Space Shuttle Orbiter Configurations at Mach Number 8

Abstract

Heat transfer tests were conducted on two Space Shuttle configurations at Mach number 8 to investigate the effects of nose geometry on windward and leeward heating and boundary layer transition. Free-stream Reynolds number based on model length was varied from 1.5 to 7.5 million at angles of attack from 20 to 50 deg. Windward centerline heating rates were in general agreement with calculated values except for laminar rates dowstream of the wing/ body junction. Differences in the location of the beginning of transition and the length of the transition zone were observed for the two configurations, but it was not clear whether variation in nose shape per se or the abrupt cross- sectional change from the nose to the aft fuselage and wing was the controlling factor.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1974
Accession Number
AD0772687

Entities

People

  • W. R. Martindale

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Transition
  • Data Reduction
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Geometry
  • Heat Transfer
  • Layers
  • Mach Number
  • Manned Spacecraft
  • Reynolds Number
  • Space Shuttles
  • Spacecraft
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster