Computation of inviscid transonic internal flow
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.
KeywordsMach Number Internal Flow Transonic Flow Outflow Boundary Supersonic Region
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