SUPERSONIC AERODYNAMIC HEATING OF A YAWED SPHERE-CONE WIND-TUNNEL MODEL

Abstract

The steady-state pressure and heat-transfer distributions on a sphere-cone configuration with laminar boundary layer have been determined in a wind tunnel at yaw angles, 0 degree and 6 degrees, and at nominal Mach numbers, 3 and 5. Comparison of the 0 degree yaw local heat-transfer rates with those of the windward body streamline at 6 degrees yaw show a maximum increase for corresponding body stations of approximately 100 percent. The 0 degree yaw heat-transfer results show good agreement with the recent theory of Powers and Krahn.

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Document Details

Document Type
Technical Report
Publication Date
Jun 28, 1960
Accession Number
AD0610729

Entities

People

  • A. J. Chones
  • S. M. Hastings

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Differential Equations
  • Equations
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Boundary Layer
  • Mach Number
  • Measurement
  • Munitions
  • Ordnance Laboratories
  • Stagnation Point
  • Steady State
  • Surface Temperature
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Fluid Dynamics.

Technology Areas

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