Heat Transfer and Pressure Measurement on a Concave Conic Model under Both Steady and Unsteady Hypersonic Flow Conditions.

Abstract

Heat transfer and pressure measurements have been measured on a conic configuration with a strongly concave surface and a blunt nose tip in the von Karman Institute Longshot free piston tunnel at M-15 and 20. The test flow parameters achieved closely simulated reentry aerodynamic conditions. Information derived from the measurements and also from high speed cine schlieren sequences enabled information to be derived on the effect of Mach number, Reynolds number, surface roughness and flow incidence on the flow over the model, the heat transfer distribution and stability of the flow. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1978
Accession Number
ADA069883

Entities

People

  • Bryan E. Richards

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Flow Visualization
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Hypersonic Flow
  • Mach Number
  • Measurement
  • Photographs
  • Photography
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Waves
  • Stagnation Point
  • Surface Roughness
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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