THE NUMBERICAL CALCULATION OF THE FLOW FIELD AROUND A REENTRY BODY

Abstract

The flow field around the Trailblazer I body (a sphere with a short cylindrical afterbody) was calculated for three flight conditions - 18,900 feet per second at 150,000 feet, 20,200 ft. per second at 200,000 feet, and 20,400 feet per second at 250,000 feet. The method of calculation is to guess a shock shape in the nose region and then to develop the flow field in the slightly supersonic region by the characteristic method. These data serve as input data for a calculation of the purely subsonic region. The result of this second calculation is a body shape which may be compared with the true shape and, if necessary, the assumed shock shape changed. The calculation in the purely supersonic region then proceeds to generate the flow field and shock shape downstream of the nose. These calculations have been programmed for the IBM 704.

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Document Details

Document Type
Technical Report
Publication Date
Sep 18, 1962
Accession Number
AD0601379

Entities

People

  • Alexander T. Fields
  • E. Kennedy

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Blunt Bodies
  • Bodies
  • Bodies Of Revolution
  • Bow Shock
  • Chemical Composition
  • Chemical Reactions
  • Electron Density
  • Electrons
  • Equations
  • Flow
  • Flow Fields
  • High Altitude
  • New York
  • Payload
  • Shape
  • Shock

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.
  • Plasma Physics / Magnetohydrodynamics

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight