Laser velocity measurements are conducted in a swept propfan rotor in order to investigate the local transonic flow region on the suction surface at high subsonic inlet Mach numbers. The velocity measurements are accompanied by a 3D-Navier-Stokes calculation for a selected operating point. The good agreement between computed and measured flow field gives some confidence to study the local three-dimensional passage shock on the suction surface by using the numerical procedure. Apart of the computed three-dimensional shock structure is investigated in detail. By considering streamlines it is concluded whether the shock wave is normal or oblique. The results are compared with the one-dimensional shock conditions.

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