TEST REPORT FOR PHASE III OF THE AERODYNAMIC HEATING TEST AT THE NASA LANGLEY UNITARY PLAN WIND TUNNEL,

Abstract

The primary purpose of the test was to determine the effect of variously shaped protuberances on the convective heat transfer coefficients for a flat plate in turbulent supersonic flow. The secondary objective of the test was to determine the convective heat transfer coefficients for the surfaces of the protuberance models. The model configurations tested were the plain flat plate, 2 in. x 4 in. flange, 30 deg. wedge 1/4 cylinder, 1 in. x 2 in. flange, 2.8 in. D swept cylinders, and 2.8 in. D vertical cylinders. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 02, 1959
Accession Number
AD0838727

Entities

People

  • P. S. Yip

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Coefficients
  • Energy
  • Energy Transfer
  • Flow
  • Heat Energy
  • Heat Transfer
  • Heat Transfer Coefficients
  • Heating
  • Supersonic Flow
  • Thermodynamics
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

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