Hypersonic Aeroelastic Analysis

Abstract

The aerothermoelastic characteristics of a tactical missile operating at near zero angle of attack in the low hypersonic speed range have been studies. An integrated digital computer program has been developed for the aeroelastic response of sharp-edge aerodynamically heated, cantilevered lifting surfaces representative of tactical missile fins. The nonuniform flow generated by a spherically blunted missile nose is accounted for. Based upon the application of the computer program to selected cases, recommendations are made regarding the analysis procedures. Appropriate prestress conditions are obtained from the quasi-static solution. An analytic theory is developed which can predict the nonuniform flow effects of nose bluntness in the complete hypersonic speed range up to Mach 3.

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Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1975
Accession Number
ADA028794

Entities

People

  • Bo O. Almroth
  • Francis A. Brogan
  • Gary M. Stanley
  • John A. Bailie
  • Lars E. Ericsson

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeroelasticity
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Hydrodynamics
  • Mechanical Phenomena
  • Mechanical Properties
  • Mechanics
  • Pressure Distribution
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.
  • Structural Dynamics.

Technology Areas

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