EFFECTS OF UNIT REYNOLDS NUMBER, NOSE BLUNTNESS, AND ROUGHNESS ON BOUNDARY LAYER TRANSITION

Abstract

This analysis consists of two parts. A technique is presented for measuring heat transfer rates on a model and for fixing the temperature distribution at a given value. The technique is applied to the particular case of turbulent heat transfer on a blunt body at a Mach number of 3.98.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1960
Accession Number
AD0262482

Entities

People

  • J. L. Potter
  • Jack D. Whitfield

Organizations

  • AGARD

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Computational Fluid Dynamics
  • Flow Fields
  • Fluid Dynamics
  • Jet Propulsion
  • Measurement
  • Nato
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Test Facilities
  • Turbulent Flow
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.