An Analytical Investigation of Viscous Shock-Layer Flow near the Leading Edge of Slender Bodies under Low-Density Hypersonic Conditions

Abstract

An analytical investigation and a numerical procedure are presented for calculating the fully viscous shock-layer flow near the sharp leading edge of both two-dimensional and axisymmetric slender bodies uses an implicit finite-difference technique in conjunction with wall slip boundary conditions; the shock structure is determined as part of the resulting solution. The mathematical model involves a more complete and accurate set of governing equations and boundary conditions.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1973
Accession Number
AD0762505

Entities

People

  • J. R. Maus

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Axisymmetric Flow
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Computers
  • Difference Equations
  • Differential Equations
  • Equations Of Motion
  • Geometry
  • Heat Transfer
  • Leading Edges
  • Low Density
  • Mathematical Models
  • Slender Bodies
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers