Formulation of the Three Dimensional Transonic Unsteady Aerodynamic Problem.

Abstract

Unsteady transonic flow for a swept wing of moderate sweep is formulated in the small disturbance limit. Boundary conditions at the wing, the trailing vortex sheet, and the outer computatinal boundaries are given including the ventilated wall conditions. Shortcomings of the small disturbance hypothesis is reviewed, suggesting means to compensate for them. Viscous interactions are described together with procedures to incorporate their effects. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1979
Accession Number
ADA075403

Entities

People

  • H. Yoshihara

Organizations

  • Boeing Military Aircraft

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Aspect Ratio
  • Boundary Layer
  • Boundary Layer Flow
  • Cartesian Coordinates
  • Differential Equations
  • Far Field
  • Fluid Dynamics
  • Inviscid Flow
  • Pressure Distribution
  • Shape
  • Three Dimensional
  • Transonic Flow
  • Turbulent Boundary Layer
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.