Location of Detailed Shock Wave in Front of a Body Moving at Supersonic Speed

Abstract

It is shown that for velocities slightly in excess of sonic, the position of detached shock wave located in front of a given body at zero angle of attack may be estimated theoretically to a reasonable degree of accuracy. In case of bodies of revolution the result was simple, but for two-dimensional bodies, pressure coefficient varies with Mach number, and slight difficulty appears. Theory developed compares favorably with available experimental data.

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Document Details

Document Type
Technical Report
Publication Date
May 06, 1947
Accession Number
ADA800635

Entities

People

  • Edmund V. Laitone
  • Otway O'm. Pardee

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Bodies
  • Bodies Of Revolution
  • Boundary Layer
  • Coefficients
  • Flow
  • Flow Fields
  • Fluid Flow
  • Free Stream
  • Mach Number
  • Perturbation Theory
  • Perturbations
  • Revolutions
  • Shock
  • Shock Waves
  • Supersonic Flow
  • Waves

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow