METHODS OF APPROXIMATING INVISCID JET BOUNDARIES FOR HIGHLY UNDEREXPANDED SUPERSONIC NOZZLES

Abstract

Methods of approximating inviscid boundaries of jets exhausting from axisymmetric supersonic nozzles into a quiescent atmosphere and moving streams have been developed. Jet shapes from two typical afterbody configurations were calculated for various flight conditions. Good agreement with available theoretical and experimental data was obtained. A step-by-step calculational procedure is given in the Appendix.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1962
Accession Number
AD0275641

Entities

People

  • J. E. Robertson
  • J. R. Henson

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Afterbodies
  • Agreements
  • Air Force
  • Atmospheres
  • Base Pressure
  • Bodies
  • Boundaries
  • Compressible Flow
  • Data Analysis
  • Exhaust Gases
  • Experimental Data
  • Free Stream
  • Jet Flow
  • Mach Number
  • Nozzles
  • Supersonic Nozzles
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow