POSTFLIGHT (AS-202) APOLLO COMMAND MODULE AERODYNAMIC SIMULATION TESTS

Abstract

A comprehensive postflight wind tunnel investigation of the Apollo Command Module was conducted to resolve several anomalies between flight (AS- 202) and preflight aerodynamic data. Attention was focused on (1) simulating the actual vehicle 'as flown', (2) obtaining consistent pitch plane force measurements in the angle-of-attack range 150 < or = alpha < or = 180 deg, (3) the effect of Mach number over a range of 3 to 20, (4) the effect of Reynolds number, and (5) possible sting effects. Results indicated that prior failure to duplicate the asymmetrical wavy heat shield in preflight testing resulted in a significant error in trim angle-of-attack prediction. In addition, a strong viscous influence was found to extend down to an altitude of about 220,000 ft. Also, a Mach number influence to a value of about 14 was found which is substantially higher than previous blunt body investigations have indicated. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1968
Accession Number
AD0666927

Entities

People

  • B. J. Griffith
  • D. E. Boylan

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Air Force
  • Altitude
  • Blunt Bodies
  • Bodies
  • Electric Arcs
  • Free Flight
  • Heat Shields
  • Mach Number
  • Measurement
  • Reynolds Number
  • Shock Tunnels
  • Test Facilities
  • Trim Angle
  • Wind Tunnel Models
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aviation Science / Aeronautics.
  • Software Engineering