The Numerical Computations of Supersonic Flow Past Blunt Bodies.

Abstract

Methods for computing numerically the flow past blunted bodies travelling at supersonic speed are developed, using finite difference schemes. The algorithms were constructed to deal with 2-D axisymmetric and 3-D configurations. Various configurations were investigated and the flow field around them computed. Comparison with available semi-empirical results for blunted cones at Mach number 3 shows good agreement. The 3-D algorithm was applied to an axisymmetric configuration and the results thus obtained show good agreement with the axisymmetric calculation. All the calculations are for the inviscid gas-dynamic case. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1976
Accession Number
ADA037665

Entities

People

  • Saul S. Abarbanel

Organizations

  • Tel Aviv University

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Blunt Bodies
  • Bodies
  • Cartesian Coordinates
  • Computational Fluid Dynamics
  • Computations
  • Differential Equations
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Mach Number
  • Partial Differential Equations
  • Shock Waves
  • Supersonic Flow
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight