Numerical Solution of Subcritical Flow Past Airfoils

Abstract

A finite-difference solution technique has been developed for subsonic two-dimensional inviscid flow past lifting airfoils. This work is an adaptation of the method used by Sells (1967). The full governing equations of compressible flow are written in terms of a translated velocity potential which is continuous throughout the flow field. This simplifies solutions for bluff airfoils (no Kutta condition) where both angle of attack and lift coefficient are specified. The computational plane is the interior of a unit circle obtained by mapping the flow field into the interior of the circle. A line over relaxation matrix method is used for solution of the partial differential equation which in the iteration scheme is coupled with an algebraic equation. The numerical procedure is accurate and well behaved for all subsonic flow conditions.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1973
Accession Number
ADA046619

Entities

People

  • David W Taylor
  • Ernest O. Rogers

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Compressible Flow
  • Computations
  • Computer Programs
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Incompressible Flow
  • Mach Number
  • Pressure Distribution
  • Simultaneous Equations
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Calculus or Mathematical Analysis
  • Computational Fluid Dynamics (CFD)