An inviscid/viscous interacton method has been developed to predict the blade-to-blade flow in transonic compressor cascades. The method intends to be used primarily for relatively high camber blades where the suction surface boun-dary layer may be slightly separated near the trailing edge. The inviscid flow was calculated by means of AF2 finite-difference scheme on a newly constructed H-type grid system[3]

and the viscous flow by the aid of an integral method for laminar and turbulent boundary layers[6] . An integration calculation was then carried out to determine the blade deviation angle and the total pressure loss coefficient. One of the authors has been involved in the recent transonic experimental work of one set of MCA cascades in Sichuan.The numerical predictions obtained have been compared with test data on four different transonic cascades in reasonably good agreement.