PRESSURE AND HEAT-TRANSFER DISTRIBUTIONS ON EXIT AND RE-ENTRY CONFIGURATIONS OF THE GEMINI SPACECRAFT AT MACH NUMBER 8 AND 10

Abstract

Selected results are presented from heat-transfer pressure distribution tests of the Gemini exit and re-entry configurations and a hemisphere-cylinder configuration in the hypersonic regime. The effects of configuration, model attitude, and Reynolds number variation on heat-transfer and pressure distributions on the Gemini vehicle were investigated. The tests were conducted at Mach numbers of 8 and 10 and various free-stream Reynolds numbers. The angle- of-attack range was from -40 to 40 deg. at selected angles of yaw from 0 to 20 deg.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1963
Accession Number
AD0337619

Entities

People

  • G. H. Merz
  • O. R. Pritts

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Bodies
  • Boundary Layer
  • Data Reduction
  • Equations
  • Fabrication
  • Flow
  • Free Stream
  • Geometry
  • Governments
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Stagnation Pressure
  • Wind Tunnels

Readers

  • Aerospace Test and Evaluation
  • Fluid Dynamics.
  • ballistics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster