Investigation of Three-Dimensional Flow Separation on Fuselage Configurations.

Abstract

A method is described for calculating the complete pressure distribution on a body with separated flow. The boundary layer characteristics are calculated along several streamlines up to the point where separation is predicted. The separated flow is modeled by streamwise panels of uniform vorticity attached to the body near the predicted separation line. Comparisons are presented of calculated and experimental pressure distributions for a cylinder, a sphere and the BO105 fuselage. The results are in fair agreement, but there are certain features of the results and restrictions of the source/vortex inviscid model which need improvement. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1977
Accession Number
ADA039382

Entities

People

  • Brian Maskew
  • Frank A. Dvorak
  • Frank A. Woodward

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Area Suction
  • Base Pressure
  • Boundary Layer
  • Computational Science
  • Coordinate Systems
  • Dense Inert Metal Explosives
  • Flow Fields
  • Geometry
  • Insensitive Explosives
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Skin Friction
  • Stratified Fluids
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Mechanics and Fluid Dynamics.