In supersonic nozzles, changing pressure ratio varies not only flow conditions but also noises. In order to clarify the relationships between noises and flows (such as shock waves and separation), the present study was conducted using the Fourier Analysis of aerodynamic noises and the Schlieren method. From the investigation, it was found that when the flow was separated from one side of the nozzle, the peak of the spectrum of the frequency response was at around 2000Hz. However, when the flow was in the whole area, the peak of the spectrum was at around 5000Hz.
- Fluids Engineering Division
Experimental Study of Aeroacoustics in Supersonic Nozzles
Okamoto, K, & Shimura, K. "Experimental Study of Aeroacoustics in Supersonic Nozzles." Proceedings of the ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. Volume 2: Symposia and General Papers, Parts A and B. Montreal, Quebec, Canada. July 14–18, 2002. pp. 289-294. ASME. https://doi.org/10.1115/FEDSM2002-31423
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