Application of the Method of Integral Relations (MIR) to Transonic Airfoil Problems. Part 2. Inviscid Supercritical Flow About Lifting Airfoils with Embedded Shock Wave

Abstract

Numerical procedures developed in a previous part of the report for applying the method of integral relations to transonic airfoil problems are extended to lifting cases. A modification enables any desired number of strips and size of integration domain to be used. Full inviscid flow equations are approximated by second-order polynomials in transverse direction in a physical plane. Numerical procedures including iterative processes are formulated for the case of high subsonic free-stream Mach numbers. Cartesian coordinates are employed except near the leading edge region where the use of a body coordinate system is convenient. Results are presented for supercritical flows past various airfoils, including two conventional, one advanced, and two shockless airfoils.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1972
Accession Number
AD0755762

Entities

People

  • David W Taylor
  • Tsze C. Tai

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Airfoils
  • Boundary Layer
  • Boundary Value Problems
  • Cartesian Coordinates
  • Computational Fluid Dynamics
  • Computational Science
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Geometry
  • Inviscid Flow
  • Mach Number
  • Pressure Distribution

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)
  • Linear Algebra