HYPERSONIC FLUTTER MODEL RESULTS AND COMPARISON WITH PISTON THEORY PREDICTIONS

Abstract

A series of flutter model tests were conducted in the Mach number range 5 to 8 to provide flutter trends and evaluate theoretical flutter prediction methods. The tests were on rectangular planform models in AEDC Tunnel E-2. Experimental results were obtained on flutter effects from varying Mach number, uncoupled frequency ratio, center of gravity, thickness ratio, profile shape, and aspect ratio. Results and trends, presented in terms of flutter velocity index, are compared with flutter data predicted by piston theory aerodynamics. Interesting results concerning the effects of structural damping on hypersonic flutter characteristics and relative flutter characteristics for hypersonic and lower speed ranges are presented. Using piston theory for predicting hypersonic flutter speeds is evaluated, and improvements in theoretical procedures are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1961
Accession Number
AD0328509

Entities

People

  • Dale E. Cooley
  • Richard P. White Jr.

Organizations

  • Calspan

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamics
  • Aeronautical Laboratories
  • Air Force
  • Aspect Ratio
  • Center Of Gravity
  • Dynamics
  • Fluid Dynamics
  • Frequency
  • Government Procurement
  • Governments
  • Gravity
  • Leading Edges
  • Mach Number
  • Test Facilities
  • United States
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow