A Rapid Graphical Method for Computing the Pressure Distribution at Supersonic Speeds on a Slender Arbitrary Body of Revolution

Abstract

A method is presented by which the pressure distribution on a slender, arbitrary body of revolution moving at supersonic speed at zero angle of attack may be calculated with an appreciable saving of time as compared with that required by other methods. The method was developed from the linearized potential-flow relations given by Jones and Margolis in NACA TN No. 1081 an(1 is essentially a graphical computing technique based on the assumption that a body may be represented satisfactorily by a relatively small number of point sources and sinks. An example is presented to illustrate the computational procedure.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1949
Accession Number
ADA380887

Entities

People

  • Jim R. Thompson

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aeronautical Laboratories
  • Aircrafts
  • Bodies
  • Bodies Of Revolution
  • Coefficients
  • Computations
  • Fineness Ratio
  • Flow
  • Low Drag
  • Low Drag Airfoils
  • Mach Number
  • Measurement
  • Parabolic Bodies
  • Pressure Distribution
  • Slender Bodies
  • Supersonic Aircraft

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow