LOCAL AERODYNAMIC HEAT TRANSFER AND BOUNDARY-LAYER TRANSITION ON ROUGHENED SPHERE-ELLIPSOID BODIES AT MACH NUMBER 3.0

Abstract

Experimental heating rates and pressure distributions obtained from aerodynamic heating tests on four steel sphere-ellipsoid bodies with surface roughnesses of 5, 100, and 200 microinches are presented. Free- tream Reynolds numbers based on model spherical diameter, were 4.25 x 10 to the 6th power and 2.76 x 10 to the 6th power, and the stagnation temperature was 650 F. The tests showed that the combination of surface roughness and boundary-layer cooling tend d to promo e arly ra sition and nullify the advantages attributable to the blunt shape of the model for reducing local temperatures. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1961
Accession Number
AD0261368

Entities

People

  • Robert W. Walker
  • William D. Deveikis

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Bodies
  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Ellipsoids
  • Fluid Mechanics
  • Heat Energy
  • Heat Transfer
  • Layers
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Roughness
  • Stagnation Temperature
  • Surface Roughness

Fields of Study

  • Physics

Readers

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