Steady/Oscillatory, Supersonic/Hypersonic Inviscid Flow Past Oscillating Wings and Wedge Combinations at Arbitrary Angles of Attack.

Abstract

The perturbation method proposed by Professor Hui is described. The method gives exact solutions for the perturbed flow over both sides of a flat plate which is oscillating with small amplitude and frequency at large angles of attack in steady supersonic/hypersonic inviscid flow provided that the shock remains attached. Using the strip theory concepts these solutions are extended to study the dynamic stability in pitch of a flat, periodically oscillating wing arbitrary planform shape, at large angles of attack. Finally, Hui's perturbation method is extended on a stationary wedge. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1981
Accession Number
ADA107438

Entities

People

  • Evangelos Vlassios Youroukos

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Value Problems
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Energy Transfer
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Frequency
  • Geometry
  • Inviscid Flow
  • Shock Waves
  • Steady Flow
  • Three Dimensional
  • Two Dimensional
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers