Abstract
A new procedure for a numerical analysis of incompressible potential flow through cascades of airfoils with arbitrary cross-sections has been presented. The procedure consists of three steps. First, airfoil rows in a physical plane are mapped into near-circle rows using a simple mapping function; then the flow field through the near-circles on the mapped plane is calculated with the singularity method. Finally, the flow on the mapped plane is transformed to that through the cascades of airfoils. The method for determination of a parameter of the mapping function to obtain near-circles with sufficiently smooth contours on the mapped plane, which is indispensable to achieving the highest accuracy in the calculation with the singularity method, has been proposed. The validity of this procedure is demonstrated by comparing the present results with exact solutions, which indicates that the method proposed is very useful for the numerical analysis of the cascades flow with simple thin airfoils as well as many practical airfoils with a camber and thickness.
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