The paper presents an entirely novel theoretical solution of inviscid flow past two-dimensional cascades of aerofoils at high subsonic velocities. The solution is carried out in the physical plane by the help of transformation equations derived for streamline coordinates. The transformation equations define the dependence between the flow fields in the regions of incompressible and compressible flows past the cascade. Knowing the incompressible flow, one can calculate the velocity distribution on an aerofoil and the outlet flow angle of the cascade in a comparatively simple way. The method makes it possible to determine the critical Mach number of the cascade with ease. The requisite computer time is relatively short. The results obtained by the new method show a very good agreement with those of other authors and with experiments.
A Theoretical Solution of Quasi-3D Compressible Flows in Turbomachines : 2nd Report, Flows on an Assumed S2 Stream Surface
