A design method for two‐dimensional cascades of turbomachinery blades is presented. A finite element potential flow program is extended to allow fluid to transpire through the blade surface, the displaced surface streamline defining a new blade geometry. The potential changes are related linearly to the transpired flow rates. New surface velocities may then be specified as a function of surface distance, in accordance with boundary layer considerations. Closure and smoothness of the new blade are successfully achieved, while large changes in the blade geometry are possible.
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Hart et al. (1987) studied this question.
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