A Modification to the Method of Garabedian and Korn

  • R. C. Lock
Part of the Notes on Numerical Fluid Mechanics book series (NONUFM, volume 3)


A modification is described to the method of Garabedian and Korn for calculating the potential flow round aerofoils. When the flow is supercritical and shock waves are present, the modification enables a solution to be obtained intermediate between the two extremes — non-conservative (N-C) and conservative (C) — of the existing method. A parameter λ (between 0 and 1) is introduced which leads to a N-C solution of λ = 0 and to a C solution if λ = 1, while taking an intermediate value allows the solution to be adjusted so that the pressure jump across the shock wave is a reasonable approximation to the true physical (Rankine-Hugoniot) jump. In this way it is hoped to achieve an overall solution which is closer to a solution of the full Euler equations while retaining the computational speed of the Garabedian and Korn method.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. 1.
    P.R. Garabedian D.G. Korn Analysis of transonic aerofoils. Comm. Pure App. Math., Vol 24, pp 841–851 (1971)Google Scholar
  2. 2.
    F. Bauer P.R. Garabedian D.G. Korn Supercritical wing sections. (Lecture notes in economics and mathematical systems, No 66) Springer-Verlag (1972)Google Scholar
  3. 3.
    F. Bauer P.R. Garabedian D.G. Korn A. Jameson Supercritical wing sections II. (Lecture notes in economics and mathematical systems, No 108) Springer-Verlag (1975)Google Scholar
  4. 4.
    A. Jameson Numerical computation of transonic flows with shock waves. Symposium Transsonicum II, p 384, Springer-Verlag (1975)Google Scholar
  5. 5.
    E.M. Murman Analysis of embedded shock waves calculated by relaxation methods. Proc. AIAA Computational Fluid Dynamics Conference, Palm Springs, July 1973Google Scholar
  6. 6.
    M.R. Collyer R.C. Lock Improvements to the viscous Garabedian and Korn method (VGK) for calculating transonic flow past an aerofoil. RAE Technical Report 78039 (1978)Google Scholar
  7. 7.
    J.L. Steger B.S. Baldwin Shock waves and drag in the numerical calculation of isentropic transonic flow. NASA TND-6997 (1972)Google Scholar
  8. 8.
    K. Oswatitsch J. Zierep Das problem des senkrechten stosses an einen gekrümmten wand. ZAMM 40, p 143 (1960)Google Scholar
  9. 9.
    C.C.L. Sells Numerical solutions of the Euler equations for transonic flow past a lifting aerofoil. Paper to be presented at GAMM Workshop, Stockholm, September 1979Google Scholar

Copyright information

© Springer Fachmedien Wiesbaden 1981

Authors and Affiliations

  • R. C. Lock
    • 1
  1. 1.Aerodynamics DeptRoyal Aircraft EstablishmentFarnborough, HampshireEngland

Personalised recommendations