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This article discusses an aerodynamic inverse design method for turbomachinery cascades. The method prescribes the mass-averaged swirl schedule and blade thickness distribution. It then determines the blade shape that accomplishes this loading by imposing the appropriate pressure jump across the blades and ensuring flow tangency to the blade surfaces. The method is validated for a compressor cascade and used to design an impulse cascade and redesign the ONERA cascade. It is implemented in a cell-vertex fini

Author

ali

Language

EN