High Reynolds Number, Low Mach Number, Steady Flow Field Calculations over a NACA 0012 Airfoil Using Navier-Stokes and Interactive Boundary Layer Theory.

Abstract

A Navier-Stokes code, developed by N.L. Sankar, and an Interactive Boundary Layer code, developed by Tuncer Cebeci, are implemented for high Reynolds number, low Mach flows over a NACA 0012 airfoil. Upper surface pressure distribution, coefficients of lift, coefficients of friction, and velocity profiles obtained from the Navier-Stokes code are compared to results obtained from the Cebeci Interactive Boundary Layer code for steady flow. The steady state cases investigated are at .3 Mach and Reynolds numbers of 1 to 5 million and at .12 Mach and a Reynolds number of 1.5 million. Keywords: Navier Stokes, Interactive boundary layer theory, Lift coefficient, Velocity profiles.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1987
Accession Number
ADA189871

Entities

People

  • Lisa J. Cowles

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations Of Motion
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Hydrodynamics
  • Mechanical Properties
  • Mechanics
  • Navier Stokes Equations
  • Steady Flow
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.