The primary aim of this study is to investigate the buzz phenomenon and its onset mechanism in a supersonic air inlet by analyzing wind tunnel test data. The inlet under examination is an axisymmetric and mixed-compression inlet designed for a Mach number of 2. To examine the effects of boundary layer suction on changing the mechanism and characteristics of the buzz phenomenon, applying the slot and porous suctions has also been investigated. The results show that the inlet without the bleed has no little buzz, and the buzz starts as the big buzz according to Dailey’s criterion. With the application of the boundary layer suction method, the buzz oscillations are not only significantly delayed, but the buzz type also changes to the little buzz according to the Ferri criterion. A comparison of slot and porous bleeds shows that the slot bleed performs better in both delaying the buzz phenomenon and reducing the amplitude of oscillations.

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