Advertisement

The method of decomposition applied in transonic flow calculations

  • K. R. Karlsson
  • Y. C. -J. Sedin
Communications
Part of the Lecture Notes in Physics book series (LNP, volume 59)

Abstract

This paper presents some results concerning recent developments of a special numerical technique, here applied to external transonic flow problems. The potential equation to be solved is of mixed elliptic-hyperbolic type and nonlinear. The basic idea is the decomposition of the original velocity potential into two new functions forming a coupled system, which can be integrated in opposite lateral directions. The two new equations are integrated, one at a time, by a marching procedure, alternating between the flying object and a chosen outer boundary at which a far field relation is assumed. The new functions are solved iteratively until convergence has been obtained. The method is based on finite difference approximations. Axisymmetric bodies and wing-body combinations have been treated.

Keywords

Transonic Flow AIAA Journal Axisymmetric Body Wing Vortex Embed Shock 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    Berndt, S.B. and Sedin, Y.C-J.: “A numerical method for transonic flow fields”. ICAS Paper 70-13, Rome, Sept. 1970.Google Scholar
  2. 2.
    Sedin, Y.C-J,: “Axisymmetric sonic flow computed by a numerical method applied to slender bodies”. AIAA Journal, April 1975, p.p. 504–511.Google Scholar
  3. 3.
    Sedin, Y.C-J. and Karlsson, K.R.: “Some numerical results of a new threedimensional transonic flow method”. Proc. IUTAM Symposium Transsonicum II, Göttingen, Sept. 8–13, 1975.Google Scholar
  4. 4.
    Murman, E.M. and Cole, J.D.: “Calculation of plane steady transonic flows”. AIAA Journal, Jan. 1971, p.p. 114–121.Google Scholar
  5. 5.
    Murman, E.M.: “Analyses of embedded shock waves calculated by relaxation methods”. AIAA Journal, May 1974, p.p. 626–633.Google Scholar
  6. 6.
    Marchuk, G.I.: “0n the theory of the splitting up method”. Symp. on the Numerical Solution of Partial Differential Eq., 1970. Ed. by B. Hubbard, Academic Press 1971, NewYork-London.Google Scholar
  7. 7.
    Loving, D.L. and Estabrooks, B.B.: “Analysis of pressure distribution of wing-fuselage configuration having a wing of 45° sweepback, aspect ratio 4, taper ratio 0.6, and NACA 65AO06 airfoil section”. NACA RM L51F07, 1951.Google Scholar
  8. 8.
    Bailey, F.R. and Ballhaus, W.F.: “Comparisons of computed and experimental pressures for transonic flows about isolated wings and wing-fuselage configurations”. NASA SP-347 Part II, March 4–6, 1975.Google Scholar
  9. 9.
    Drougge, G.: “An experimental investigation of the interference between bodies of revolution at transonic speeds with special reference to the sonic and supersonic area rules”. The Aeronautical Research Inst. of Sweden, Report 83, Stockholm 1959.Google Scholar

Copyright information

© Springer-Verlag 1979

Authors and Affiliations

  • K. R. Karlsson
    • 1
  • Y. C. -J. Sedin
    • 1
  1. 1.Aerospace DivisionSAAB-SCANIA ABLinköpingSweden

Personalised recommendations