Heat-Transfer and Flow-Field Tests of the North American Rockwell/ General Dynamics Convair Space Shuttle Configurations

Abstract

Aerothermodynamic tests of Phase B space shuttle configurations proposed by North American Rockwell/General Dynamics Convair were conducted at Mach number 8. Test conditions provided both Mach number and Reynolds number simulation for typical ascent and reentry trajectories. This report provides a comprehensive analysis of the major test results and also presents data comparisons with theoretical calculations. Specific areas covered are: ascent heating and shock interference, booster reentry heating and flow fields, and orbiter reentry including leeside heating, windward shock angles and flow fields, windward surface heating, and boundary-layer transition.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1973
Accession Number
AD0755354

Entities

People

  • L. L. Trimmer
  • R. K. Matthews
  • W. R. Martindale

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Cameras
  • Data Reduction
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Mach Number
  • Photographs
  • Pressure Distribution
  • Reynolds Number
  • Space Shuttles
  • Test And Evaluation
  • Turbulent Flow
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Fluid Mechanics and Fluid Dynamics.
  • Missile Defense Systems.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris