EFFECTS OF COOLING ON TRANSITION IN THE BOUNDARY LAYER ON A HEMISPHERE IN SIMULATED HYPERSONIC FLOW

Abstract

A study was made to investigate the effects of cooling on transition in the boundary layer on the nose of a 9-inch diameter hemisphere in simulated hypersonic flow, with the aim of gaining some knowledge of the circumstances under which boundary-layer cooling may promote a reduction in transition Reynolds number (transition reversal). The influences of cooling in increasing the stability to Tollmien-Schlichting type disturbances, in decreasing any stabilizing effects of convex curvature, and in increasing the magnitude of disturbances from fixed roughness elements, are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1961
Accession Number
AD0256234

Entities

People

  • A. M. Kuethe
  • Roger Dunlap

Organizations

  • University of Michigan

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Control
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Computational Fluid Dynamics
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Hydrodynamics
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Shock Tubes
  • Surface Roughness
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers