Computational Investigation of the Compressible Dynamic Stall Characteristics of the Sikorsky SSC-A09 Airfoil

Abstract

Steady and unsteady two-dimensional flowfield analysis was conducted for a Sikorsky SSC-AO9 airfoil in compressible, high Reynolds number flows. Limited verification with experimental measurement was achieved. Computational methods included a steady, linear panel method with compressibility corrections; a laminar and turbulent boundary layer method; an unsteady, linear panel method; and a numerical solution method of the thin layer, compressible, Navier-Stokes equations using a body-fitted C-type computational grid. The Baldwin-Lomax, two- layer, zero-equation turbulence model was used. Wind tunnel wall interference effects were ignored. Steady and unsteady airloads and instantaneous flow pictures are presented. In steady flow with little or no separation, computed lift, drag, pitching moment, and skin friction coefficients, as well as displacement thickness and boundary layer velocity profiles at several angles- of-attack were generally found to be in good agreement with experimental data.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1993
Accession Number
ADA274867

Entities

People

  • Thomas A. Johnston

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Differential Equations
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Mechanical Properties
  • Navier Stokes Equations
  • Pressure Distribution
  • Reynolds Number
  • Steady Flow
  • Turbulent Mixing
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.