Abstract
At transonic flow conditions, unsteady self-excited shock waves are frequently observed in several modern internal aeronautical applications such as in turbine cascades, compressor blades, butterfly valves, fans, nozzles, diffusers and so on. The appearance of shock oscillation often causes serious problems such as aero-acoustic noise, non-synchronous vibration (NSV), intense drag rise, high cycle fatigue failure (HCF) and buffeting. In recent years, the effect of various passive means on the airfoil are investigated both experimentally and numerically to find the effectiveness as a shock control device. In the present study, the transonic internal flow around an airfoil using a cavity as a passive means of shock control was investigated numerically. Computational results are validated with available experimental data. Results showed that the airfoil with cavity significantly reduced the flow field unsteadiness such as the amplitude of pressure oscillation and root mean square of pressure oscillation.
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