Stagnation Point Solution of Viscous Shock Layer Equations for Flow Past a Sphere

Abstract

Numerical solutions in the stagnation region of a spherically blunted body are obtained by using the full and thin layer version of the viscous shock layer equations. The numerical system utilizes an implicit finite difference scheme combined with a relaxation technique for determining the bow shock shape. Comparisons with experimental data are made for shock Reynolds numbers, Re sub s, of 20 to 2000 and Mach numbers of 4 to 20. Both the surface heating levels as well as the shock layer density profiles are presented. It is found that with the inclusion of the shock and body slip, the full viscous shock layer model apparently enjoys a range of validity down to Re sub s of 20 to 30. The thin layer version of these equations are shown to be inadequate for such low Reynolds numbers.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1976
Accession Number
ADA028079

Entities

People

  • B. N. Srivastava
  • M. J. Werle
  • R. T. Davis

Organizations

  • University of Cincinnati

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Chebyshev Polynomials
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Heat Transfer
  • Hypersonic Flow
  • Mach Number
  • Mechanics
  • Navier Stokes Equations
  • Physical Properties
  • Reynolds Number
  • Shock
  • Stagnation Temperature

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)