Shock Wave Turbulent Boundary Layer Interaction in Hypersonic Flow

Abstract

A study is presented of the characteristics of transitional and turbulent layers, and regions of shock wave-turbulent boundary layer interaction in high Reynolds number hypersonic flow. An examination and correlation of skin friction, heat transfer and pressure measurements in laminar, transitional and turbulent boundary layers on sharp flat plates and cones are presented for the Mach range from 3 to 13 at wall-to-free stream temperature ratios from 0.1 to 0. 4.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA014742

Entities

People

  • Michael S. Holden

Organizations

  • Calspan

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Data Storage Systems
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Hydrodynamics
  • Measurement
  • Mechanics
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Skin Friction
  • Three Dimensional
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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