THE EXTENT OF LAMINAR, TWO-DIMENSIONAL BOUNDARY LAYER SEPARATION DUE TO A COMPRESSION CORNER AT MODERATELY HYPERSONIC SPEEDS

Abstract

A simple technique is presented for estimating the extent of separation of a two-dimensional laminar boundary layer including effects of Mach number, Reynolds number, and heat transfer. Quantitative effects of these parameters are discussed for moderately hypersonic speeds.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1969
Accession Number
AD0686818

Entities

People

  • Karlheinz O. Ball

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Department Of Defense
  • Experimental Data
  • Fluid Dynamics
  • Fluid Mechanics
  • Government Procurement
  • Governments
  • Layers
  • Mach Number
  • Mechanics
  • Pressure Distribution
  • Reynolds Number
  • Stagnation Temperature
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Ocean-Atmosphere Mesoscale Modeling, Data Assimilation, and Flux Boundary Layers

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow