SHOCK TUNNEL STUDIES OF THE AERODYNAMICS OF ATMOSPHERIC ENTRY

Abstract

Shock tunnel studies of the aerodynamic problems of current and future atmospheric entry vehicles are presented. Five major es instrumentation techniques are sed to meas re the following types of odel data: (1) surface pressure distributions, through the use of small piezoelectric crystal gages and special mounting and calibration techniques, (2) surface heat transfer distributions, through the use of thin film resistance thermometers (quantitative) and scorch models (qualitative), (3) aerodynamic forces and moments, through the use of the optical tracking of light models that are allowed to fly freely in the test flow, (4) flow field geometries through the use of high speed schlieren and shadowgraph techniques, and (5) boundary layer flow directions, inferred from surface oil streak studies. Typical experimental results are presented and discussed.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1962
Accession Number
AD0292016

Entities

People

  • C. J. Harris
  • E. M. Kaegi
  • R. E. Geiger
  • W. R. Warren

Organizations

  • General Electric

Tags

Communities of Interest

  • Advanced Electronics
  • Human Systems
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Boundary Layer
  • Films
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Instrumentation
  • Measurement
  • Piezoelectric Crystals
  • Pressure Distribution
  • Resistance Thermometers
  • Shock Tubes
  • Shock Tunnels
  • Thin Films

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

  • AI & ML
  • AI & ML - Bayesian Inference