Improvement of Mechanical Model in the Entrainment Method for Compressible Turbulent Boundary Layer,

Abstract

This paper presents an improved entrainment method for the two dimensional compressible turbulent boundary layer. This method is simple with short computer time and can be used for the development of calculations for the turbulent boundary layer behind a shock wave. Calculated results from six examples indicate that this method has excellent numerical accuracy. When compared with P. D. Smith's method, the results show a marked improvement.

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Document Details

Document Type
Technical Report
Publication Date
May 29, 1986
Accession Number
ADA168451

Entities

People

  • Hanling Bao

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircraft Wings
  • Boundary Layer
  • Equations
  • Experimental Data
  • Flow
  • Flow Fields
  • Foreign Technology
  • Layers
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Shock Waves
  • Three Dimensional
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design