Parametric Study of Hypersonic Turbulent Boundary Layers with Heat Transfer

Abstract

Models of the Reynolds shear stress and the turbulent energy flux are modified to include the effect of fluctuating density for the hypersonic flow regime. The compressible turbulent boundary layer equations are solved by a finite difference scheme. The results, indicate a meaningful improvement in predicting the skin friction coefficient. The static pressure variation across a turbulent boundary layer is also investigated in the present analysis by including the normal momentum equation. A tentative model for the fluctuating velocity term is proposed and the resulting pressure variation across the boundary layer is confirmed by experimental measurements.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1974
Accession Number
AD0778430

Entities

People

  • J. S. Shang

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Equations
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Mach Number
  • Measurement
  • Prandtl Number
  • Pressure Distribution
  • Shear Stresses
  • Skin Friction
  • Static Pressure
  • Thermal Conductivity
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers