Model for High-Speed Interaction Heating.

Abstract

A boundary-layer model with application to high-speed flow separation in compression corner geometries is described. Integration through regions of separating/reattaching flow is facilitated through the use of an inverse boundary layer procedure that computes the pressure gradient for a given boundary-layer displacement thickness and displacement mass flow. Comparisons with Navier-Stokes calculations for a confined separated flow, using the Reyhner-Flugge-Lotz approximation in the reverse flow region, are good and have served to validate the boundary-layer approach. The viscous-inviscid interaction occurring in these flows are accounted for with the physically-sound coupling scheme developed recently by Wigton and Holt. A specific algorithm for hypersonic shock wave boundary-layer interactions is developed using the Newtonian flow approximation. Future calculations appropriate to laminar and turbulent compression corner experimental data are outlined. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA127250

Entities

People

  • H. H. Legner
  • M. L. Finson

Organizations

  • Physical Sciences (United States)

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Experimental Data
  • Flow Separation
  • Fluid Dynamics
  • Geometry
  • Inviscid Flow
  • Layers
  • Mass Flow
  • Pressure Gradients
  • Secondary Flow
  • Shock Waves
  • Skin Friction
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flight