FLUTTER MODEL TESTS AT HYPERSONIC SPEEDS MACH NUMBERS 5 TO 8 (U)

Abstract

Experimental flutter data are presented in the Mach number range between 5 and 8 for configurations supplementary to those for which data are presented in the basic report. The results of correlative analyses to determine the accuracy and APPLICABILITY OF PISTON THEORY IN PREDICTING THE AEROELASTIC INSTABILITY OF THESE CONFIGURATIONS IN THIS SPEED RANGE ARE ALSO INCLUDED. A total of 32 semirigid (roll-pitch) flutter data points were obtained during the experimental phase of the program to determine the effects of Mach number, aspect ratio, leading-edge bluntness and thickness on flutter.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1961
Accession Number
AD0324391

Entities

People

  • John C. Balcerak
  • Richard P. White Jr.

Organizations

  • Calspan

Tags

Communities of Interest

  • Advanced Electronics

DTIC Thesaurus Topics

  • Air Force
  • Aspect Ratio
  • Center Of Gravity
  • Dynamics
  • Fluid Dynamics
  • Frequency
  • Government Procurement
  • Governments
  • Leading Edges
  • Mach Number
  • Model Tests
  • Semirigid
  • Stagnation Pressure
  • Thickness
  • United States
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow