EXPERIMENTAL INVESTIGATION AT MACH NUMBER 3.0 OF THE EFFECTS OF THERMAL STRESS AND BUCKLING ON THE FLUTTER OF FOUR-BAY ALUMINUM ALLOY PANELS WITH LENGTH-WIDTH RATIOS OF 10

Abstract

Tests were conducted at dynamic pressures from 1,500 psf to 5,000 psf and at stagnation temperatures from 300 to 655 F. The panels were restrained by the supporting structure in such a manner that partial thermal expansion of the skins could occur. The test results revealed that when a flat panel is aerodynamically heated its susceptibility to flutter increases due to thermal stress, but that when a buckled panel is further heated its susceptibility to flutter decreases. The reversal in the flutter trend for thermally buckled panels is attributed to the panel postbuckling behavior. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1961
Accession Number
AD0264740

Entities

People

  • George E. Griffith
  • Herman L. Bohon
  • Sidney C. Dixon

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Alloys
  • Aluminum
  • Aluminum Alloys
  • Buckling
  • Dynamic Pressure
  • Mach Number
  • Physical Properties
  • Stagnation Temperature
  • Stresses
  • Thermal Expansion
  • Thermal Stresses

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Structural Dynamics.
  • Thermal Physics or Thermal Science.