The Viscous Transonic Flow over Two-Element Airfoil Systems.

Abstract

A numerical procedure has been developed to compute the transonic viscous-inviscid interacting flow field about airfoils with leading edge slats or trailing edge flaps. The inviscid theory utilizes conformal mappings in a full potential flow formulation, with analytic removal of singularities and a mixed flow relaxation procedure. The turbulent boundary layer is computed with methods based on a turbulent kinetic energy formulation and is coupled to the inviscid flow using surface source flow boundary conditions. Semiempirical methods are used to compute local strong interaction regions occurring in the vicinity of shock waves, trailing edges, and to account for flow separation. Our results are in good agreement with existing wind tunnel data for several typical two-element airfoil configurations. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1978
Accession Number
ADA058425

Entities

People

  • B. Grossman
  • G. Volpe

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Conformal Mapping
  • Coordinate Systems
  • Flow Fields
  • Flow Separation
  • Fluid Dynamics
  • Free Stream
  • Inviscid Flow
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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