Experimental Panel Flutter Results for Some Flat and Curved Titanium Skin Panels at Supersonic Speeds

Abstract

The results of tests at Mach numbers from 1.72 to 2.62 on panels having a thickness from O.Ol5 to 0.045 inch, length-width ratio from 0.36 to 2.76, and radius-thickness ratio from 600 to infinity are presented. These results indicate a strong influence of differential pressure, which caused buckling on the flutter mode and on the dynamic pressure flutter for the curved panels. Results for both the flat and curved pan 5 fall within an extrapolation of an existing experimental panel flutter boundary.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1963
Accession Number
ADA397219

Entities

People

  • John G. Presnell Jr.
  • R. L. Mckinney

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aspect Ratio
  • Boundaries
  • Dynamic Pressure
  • Free Stream
  • Frequency
  • Instrumentation
  • Mach Number
  • Modulus Of Elasticity
  • Motion Pictures
  • Photographs
  • Pressure Regulators
  • Static Pressure
  • Tape Recorders
  • Thickness
  • Titanium
  • Variable Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Structural Health Monitoring of Composite Structures.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow