A Study of Panel Flutter Including a Turbulent Boundary Layer.

Abstract

A theory is developed for calculating flutter boundaries of a finite or infinite length array of panels in a supersonic flow including the effects of a turbulent boundary layer. The panel flutter analysis is based on the exact Laplace transform method of Zeydel and Yates. The aerodynamic theory is based on an integral perturbation method. Calculations are given for finite and infinite length panels. Very small boundary layer thickness are discussed for stabilizing the traveling wave type of flutter in a finite length panel.

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1974
Accession Number
ADA003688

Entities

People

  • John E. Yates

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Flow
  • Integrals
  • Layers
  • Mathematics
  • Perturbations
  • Supersonic Flow
  • Thickness
  • Traveling Waves
  • Turbulent Boundary Layer
  • Waves

Fields of Study

  • Physics

Readers

  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers