Visid/Inviscid Separated Flows.

Abstract

A method has been developed for calculating subsonic three-dimensional flows over fighter aircraft configurations at flow conditions including separation. The method employs a viscid inviscid interaction approach, with a panel method used for the inviscid analysis and a finite difference boundary layer method for the viscous analysis. The viscid and inviscid analyses are coupled using an interactive technique based on inverse boundary layer theory. This approach allows efficient calculation of flows with large separation regions, including both leading and trailing edge separations. The method was validated on three fighter aircraft geometries and comparisons with test data are presented. Keywords: Jet fighters; Separated flow; Viscid/inviscid interactions; Interactive boundary layer theory; Wing-body geometry; Subsonic flow.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1986
Accession Number
ADA179858

Entities

People

  • D. P. Mack
  • Kai-Chi Chang
  • R. W. Clark
  • S. M. Schimke
  • T. Cebeci

Organizations

  • McDonnell Aircraft Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Computational Science
  • Coordinate Systems
  • Fighter Aircraft
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Inviscid Flow
  • Pressure Distribution
  • Three Dimensional
  • Turbulent Mixing
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.