SUPERSONIC STAGNATION PNT HEAT TRANSFER TO HEMISPHERE CYLINDERS AT LOW REYNOLDS NUMBERS

Abstract

Stagnation point heat transfer at low Reynolds numbers in a supersonic air stream was investigated experimentally. A transient technique was employed using precooled thin-walled hemisphere-cylinder models. Tests were conducted at nominal Mach numbers of 2, 4, and 6, and in the Reynolds number range of 80 to 1500. Results are best represented by continuum boundary layer theory. Scatter was about =10%, so that any possible small shock wave-vorticity effect at the lower values of Reynolds number could not be identified.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1963
Accession Number
AD0403711

Entities

People

  • H. Tong
  • W. H. Giedt

Organizations

  • University of California, Berkeley

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Bodies
  • Boundaries
  • Boundary Layer
  • Coefficients
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Mach Number
  • Measurement
  • Reynolds Number
  • Shock
  • Stagnation Point
  • Stagnation Temperature
  • Temperature Gradients
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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