Aerodynamic Computer Code for Computing Pressure Loads on a Missile at High Supersonic Speeds and Generalized Attitudes.

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 for high supersonic speeds and generalized attitudes of the missile. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1979
Accession Number
ADA081596

Entities

People

  • Kenneth K. Wang

Tags

Communities of Interest

  • C4I
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Bodies
  • Bodies Of Revolution
  • Computer Programs
  • Computers
  • Coordinate Systems
  • Geometry
  • Leading Edges
  • Mach Number
  • Open System Architecture
  • Plastic Explosives
  • Pressure Distribution
  • Structural Analysis
  • Supersonic Flow
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computer Science.
  • Fluid Mechanics and Fluid Dynamics.
  • Missile Defense Systems.

Technology Areas

  • Hypersonics