EQUATIONS AND FORTRAN PROGRAM FOR APPROXIMATE AERODYNAMIC HEAT TRANSFER AND TRANSIENT TEMPERATURE DISTRIBUTIONS FOR LEADING EDGES AND FLAT PLATE SURFACES

Abstract

The equations and a Fortran program to calculate supersonic and hypersonic aerodynamic heat transfer rates and transient temperature distributions for spherical leading edges and flat plate surfaces are presented. The missile skin is composed of one to three different slab materials and/or thin wall combinations for flight trajectories or wind tunnel conditions. The Fortran program is written for the IBM 1620 40K digital computer.

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Document Details

Document Type
Technical Report
Publication Date
Oct 25, 1965
Accession Number
AD0476831

Entities

People

  • Alma S. Marks
  • L. H. Johnson

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Boundary Layer
  • Computer Programs
  • Computers
  • Digital Computers
  • Equations
  • Heat Transfer
  • Heat Transfer Coefficients
  • Leading Edges
  • Mach Number
  • Materials
  • Pressure Distribution
  • Skin Friction
  • Thermal Conductivity
  • Thin Walls
  • Walls
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow