Comparison of C- and O-Grid Generation Methods Using a NACA 0012 Airfoil

Abstract

An investigation is undertaken to compare the performance of C- and O-grid generation methods as applied to numerically predicting the flow about a NACA 0012 airfoil. Both types of grid were generated using a hyperbolic grid generation code. The solution of the flow field was numerically calculated using the Beam and Warming algorithm to solve the two-dimensional Navier-Stokes equations for viscous, compressible flow. Numerical solutions are obtained for Mach number ranging from 0.3 to 1.1, angle of attack ranging from 0 to 13 degress, and Reynolds numbers between 2 and 6 million. The numerical results obtained from both C- and O-grids are compared to experimental data. Results indicate a weakness is the method of applying the boundary conditions in the wake or the C-grid, while the overall resolution in the wake is poor for the O- grid due to inadequate control of grid spacing in that region. The transformation metrics are examined to explain differences observed in grid performance. Keywords: Computational fluid dynamics; Beam and warming algorithm; Navier Stokes equations; Grid generation; Theses. (jhd)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1989
Accession Number
ADA216375

Entities

People

  • Mark J. Lutton

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Mach Number
  • Navier Stokes Equations
  • Partial Differential Equations
  • Pressure Distribution
  • Reynolds Number
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.

Technology Areas

  • Space