Abstract
Well documented explicit TVD schemes are assessed in terms of time accuracy, propagation properties and computational work load with emphasis on their application to unsteady turbomachinery flow computations. Non-reflecting boundary conditions are in use for the flow entry and exit boundaries. As inviscid test cases serve the flow through a flat plate cascade excited by oscillating back pressure and the unsteady flow past an oscillating NACA-0012 profile. The shock induced turbulent boundary layer separation on an arc profile in a channel is studied qualitatively.
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