This paper reviews experience at evaluating three-dimensional shock structures for transonic/supersonic compressor rotors, including experimental results obtained by holography, laser velocimetry, and highfrequency pressure transducers. Typical shock wave angles are oblique to the relative flow with angles in the range 60-65 deg range for maximum deflection, rather than the 40-50 deg range predicted by conventional cascade analyses. Results are partially explained by obliquity of the shocks in between-blade-streamsurfaces. Procedures for generating analytical flow patterns consistent with experiment, including supersonic/subsonic transition through oblique shocks, are demonstrated.
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