Aerodynamic Computer Code for Analyzing Heat Transfer and Pressure Loads on Missiles.

Abstract

An aerodynamic computer code was developed for calculating the pressure distribution on a missile or its components, e.g., body and wings and subsequently interpolating the results by surface fit at locations as specified for structural analysis using the NASTRAN computer code. The code is valid from subsonic up to high supersonic speeds and for generalized attitudes of the missile. Subroutines have been added to the code to enable calculation of temperature histories, equilibrium temperature and heat flux at arbitrary locations on a missile. In addition, capability for treating slightly blunted nose configurations has been incorporated. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1982
Accession Number
ADA111997

Entities

People

  • Kenneth K. Wang
  • R. H. Weatherford

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Heating
  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Astronautics
  • Boundary Layer
  • Computer Programs
  • Coordinate Systems
  • Heat Transfer
  • Materials
  • Materials Laboratories
  • Mechanical Properties
  • Physics Laboratories
  • Pressure Distribution
  • Stress Analysis
  • Structural Analysis

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion science or combustion engineering.
  • Computer Science.

Technology Areas

  • Hypersonics