Dynamic Stall Calculations Using a Navier-Stokes Solver

Abstract

A Navier Stokes problem solver, is installed and verified on the Cray X/MP-48 computer and is used to calculate the flow field about a NACA 0012 airfoil oscillating in pitch. Surface pressure distributions and integrated lift, pitching moment, and drag coefficients versus angle of attack are compared to existing experimental data for two cases, involving deep dynamic stall and fully attached flow at and below a freestream Mach number of .3. The flow field about the oscillating airfoil is investigated through the study of contour plots of pressure, density, Mach number, and stream function. The effect of turbulence modeling is explored through use of the Baldwin Lomax model and a modification designed to prevent underprediction by repeating the deep stall simulation at one-tenth the experimental Reynolds number and Mach numbers of .3 and 5. The latter conditions are intended for comparison with the results of wind tunnel experiments.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1986
Accession Number
ADA178566

Entities

People

  • James F. Valdes

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Engineering
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Mach Number
  • Mechanical Properties
  • Mechanics
  • Physics Laboratories
  • Pressure Distribution
  • Reynolds Number
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.