The present paper describes an experimental and numerical works to investigate a noise phenomenon in supersonic flow that are discharged from a convergent-divergent nozzle with a constant area duct. The noise phenomenon of flow is generated by an emission of acoustic tones. The results obtained shows that unlike the frequency of the screech tone due to the shock-cell structures in the jet flow, the one of the acoustic tone due to the shock wave in the nozzle increases proportional to the nozzle pressure ratio. The frequency of the acoustic tone is depending on the distance from the shockwave to nozzle exit.
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