Turbulent Boundary Layer Heat Transfer in High Speed Flows

Abstract

Attempts at developing an improved engineering method for predicting separated supersonic turbulent flows are reported. The approach is based on the use of an inverse boundary layer method, coupled with a five-equation Reynolds stress turbulence model, comparisons of results of the turbulence model with measurements on attached boundary layers in adverse boundary layers showed that the model predicts too large an increase in the turbulent Reynolds stress. Most of the existing inverse boundary layer methods could not be readily applied to the present problem. A second approach was adopted, but proved to be not very 'robust'. Attempts to simulate separated flows failed to yield a proper separation zone, apparently due to excessive build-up of the Reynolds stress. Finally, it is noted that reliable algorithms for matching the boundary layer solution in the outer inviscid flow need to be developed.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1985
Accession Number
ADA174568

Entities

People

  • H. H. Legner
  • Michael L. Finson

Organizations

  • Physical Sciences (United States)

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Engineering
  • Equations
  • Flow
  • Fluid Dynamics
  • Heat Transfer
  • Inviscid Flow
  • Measurement
  • Pressure Gradients
  • Three Dimensional
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers