Supersonic Flutter of a Thermally Stressed Flat Panel with Uniform Edge Loads

Abstract

The effect of a nonuniform, self-equilibrating stress state associated with a parabolic temperature distribution is included in the flutter analysis of a rectangular, simply supported panel subjected to airflow over one surface and uniform edge loads. Linearized, static, two-dimensional aerodynamics is used in conjunction with thin-plate theory to formulate the problem. A Numerical results for a square panel show that nonuniform self-equilibrating stresses are as important as uniform stresses in affecting flutter behavior.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
ADA399805

Entities

People

  • Harry G. Schaeffer
  • Walter L. Heard Jr

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aerodynamic Loading
  • Amplitude
  • Cross Flow
  • Differential Equations
  • Dynamic Pressure
  • Eigenvalues
  • Equations
  • Flow
  • Mach Number
  • Mechanics
  • Modulus Of Elasticity
  • Partial Differential Equations
  • Stresses
  • Thermal Expansion
  • Thermal Stresses
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics