期刊名称：International Journal of Hybrid Information Technology
印刷版ISSN：1738-9968
出版年度：2016
卷号：9
期号：8
页码：85-94
出版社：SERSC
摘要：In order to verify the feasibility of the method of numerical simulation of supersonic noise, the flow field and noise at far field of a small solid fuel rocket engine F tested by National Aeronautics and Space Administration's Langley Research Center (NASA) was simulated by computational fluid dynamics (CFD) and computational aeroacoustics (CAA). The conjunction with large eddy simulation and FW-H integral method is adopted to simulate spectrums of the noise. The conjunction with large eddy simulation and Möhring sound analogy is adopted to predict the direction of the noise at the near-field. Comparing the result with the experimental data, the flow field coincides well, and in the sound field, the low and medium-frequency sound pressure level coincides well too, and the high-frequency sound pressure level is slightly lower than the estimated value. The error of overall sound pressure level of the measure point is small. The sound field resulted by high temperature, high pressure and high velocity fluid is simulated successfully.
