Computation of inviscid transonic internal flow

  • U. Giese
Contributed Papers
Part of the Lecture Notes in Physics book series (LNP, volume 170)


Compressible internal flows are studied with an implicit finite difference solution of the full potential equation in conservative form. For numerical stability in supersonic regions an artificial compressibility formulation is introduced. Boundary fitted curvilinear coordinates are used which are stretched in order to cope with regions of strong gradients. The equations are solved by an approximate factorization technique. Results are presented for nozzle flow and for flows through valve inlets with different wall contours. Some results are compared with Mach-Zehnder Interferograms.


Mach Number Internal Flow Transonic Flow Outflow Boundary Supersonic Region 
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Copyright information

© Springer-Verlag 1982

Authors and Affiliations

  • U. Giese
    • 1
  1. 1.Aerodynamisches InstitutRWTH AachenAachenGermany

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