Application of a Finite Difference Method to the Transonic Airfoil Problem.

Abstract

This study presents the development and evaluation of a numerical solution technique used to analyze the two dimensional transonic airfoil problem. The full potential equation of motion and the irrotationality condition are used for the governing equations. A coordinate transformation is applied to the governing equations to limit the domain of the problem and for easier application of the boundary conditions. The method of lines is then used to reduce the equations from partial to ordinary differential equations. Solutions obtained using this numerical solution technique are compared to published data for both incompressible and compressible flowfield cases. It is concluded that the solution technique developed in this study is accurate and efficient when analyzing subcritical flowfields around circular airfoil shapes. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA124720

Entities

People

  • Michael Patrick Burke

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Value Problems
  • Coordinate Systems
  • Differential Equations
  • Engineering
  • Equations
  • Flow Fields
  • Geometry
  • Hyperbolic Differential Equations
  • Incompressible Flow
  • Mach Number
  • Partial Differential Equations
  • Radial Velocity
  • Schematic Diagrams
  • Supercritical Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

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