FREE-FLIGHT RANGE TESTS OF THE APOLLO COMMAND MODULE

Abstract

Results are presented for free-flight range tests of the basic Apollo Command Module configuration (smooth heat shield) conducted in Range G at nominal Mach numbers of 6.0 and 8.5. The Reynolds number based on model diameter and free-stream conditions varied from 50,000 to 240,000. Both drag and stability data are presented in addition to trim angles of attack corresponding to three lateral center-of-gravity positions. Comparison of the results with data from wind tunnels shows at most only small sting effects on the wind tunnel data.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1969
Accession Number
AD0680396

Entities

People

  • W. R. Lawrence
  • W. S. Norman

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • C4I
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Center Of Gravity
  • Coordinate Systems
  • Data Reduction
  • Diameters
  • Differential Equations
  • Flight
  • Fluid Dynamics
  • Free Flight
  • Free Stream
  • Heat Shields
  • Mach Number
  • Measurement
  • Reynolds Number
  • Test Facilities
  • Trim Angle
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Software Engineering