Abstract
A method is presented for calculating the flowfield about a cascade of arbitrary two-dimensional blades. A conformal transformation is used to generate a finite-difference grid. Implicit approximate factorization (AF) scheme is used for the solution of matrix equations resulting from finite-difference approximation to the full potential equation in conservation form. For transonic flows, an artificial viscosity, required to maintain stability in supersonic regions, is introduced by an upwind bias of the density. This allows the simple matrix form of the schevie to be retained over the entire flowfield. Supercritical test cases are considered. Blade Mach number or pressure distributions have been computed and are in good agreement with independent results.
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