New very fast artificial time-dependent techniques for isentropic inviscid steady transonic flows are applied to turbine cascades. An explicit dissipative finite volume scheme with splitting of the space operators is used. The efficiency of the new technique is tested for turbine blades with a relatively thick rounded supersonic trailing edge, and is compared with that of other classical methods. Different models used to apply the Kutta condition and to predict the base pressure accounting for the separation occuring in that region are fully described and tested. For a comparable accuracy, the new method is found to be faster than most of the classical numerical techniques generally applied to similar problems.

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