Boundary Layer Transition on Blunt Bodies in Hypersonic Flow

Abstract

Heat transfer and pressure distributions have been measured on a family of smooth and rough 50 deg - 8 deg biconic models in the M=15 to 20, Re/ ft = 2 million to 8.5 million flow simulating re-entry flow and achieved in the von Karman Institute's Longshot facility. The test conditions were selected to generate boundary layer transition data on these models.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1975
Accession Number
ADA018805

Entities

People

  • B. E. Richards

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Mach Number
  • Materials
  • Materials Laboratories
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Stagnation Point
  • Test Facilities
  • Thermodynamics
  • Turbulent Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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