EXPERIMENTAL STUDIES OF THE UNSTEADY AERODYNAMICS OF PANELS AT OR NEAR FLUTTER WITH A FINITE BOUNDARY LAYER MACH NUMBER 1 TO 10

Abstract

This report presents the results of an experimental study of panel flutter with particular stress on definition of the aerodynamic forces involved in flutter. Panel flutter data are obtained by forced response techniques. Panel oscillating pressure and motion field measurements at or near flutter were made under known boundary layer conditions in the Mach number range of 1.1 to 10. The pressure field measurements are compared with calculated pressure fields which have been corrected for boundary layer effects. The comparisons indicate that the boundary layer has a strong effect on the amplitude and phase of the pressure field at or near flutter. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1964
Accession Number
AD0356821

Entities

People

  • Anne Brown
  • G. W. Asher

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Aerodynamics
  • Amplitude
  • Boundaries
  • Boundary Layer
  • Fluid Dynamics
  • Fluid Mechanics
  • Layers
  • Mach Number
  • Measurement
  • Unsteady Aerodynamics

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Structural Dynamics.