LOCAL AERODYNAMIC PARAMETERS FOR SUPERSONIC AND HYPERSONIC FLUTTER ANALYSES

Abstract

The report presents the results of an analysis to determine how certain aerodynamic flutter parameters are changed from their free stream values by the existence of supersonic and hypersonic nose shock waves and expansions. The results indicate that nose shock waves and expansions can create a new set of 'free stream' conditions for flutter analyses. These new free stream conditions can be sufficiently different from the undisturbed 'free stream' condition to warrant their detailed analyses in the supersonic and hypersonic vehicle.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0626928

Entities

People

  • James J. Olsen

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Aircrafts
  • Blast Waves
  • Coefficients
  • Dynamic Pressure
  • Experimental Data
  • Flight
  • Flow
  • Free Stream
  • Hypersonic Aircraft
  • Mach Number
  • Shock Waves
  • Static Pressure
  • Supersonic Flow
  • Two Dimensional
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow