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所属单位：航空学院

发表刊物：Zhendong Gongcheng Xuebao

摘要：The Non-Linear Acoustic Solver(NLAS) is employed to study the cavity noise in supersonic combined with Reynolds-averaged Navier-Stokes(RANS) equation. It is shown by the comparison between the calculated results and the WICS wind tunnel tests when the Mach number is 2, the sound pressure level of every monitoring point is in good agreement with experiments. It indicate that the NLAS method which is based on turbulence reconstruction could well simulate the cavity noise in supersonic and reduce mesh numbers. The cavity noise with large curvature edge is researched. The maximum sound pressure level is 162dB when the Mach number is 2.5, and so the corresponding noise reduction measure should be adopted, otherwise the structure damage will occur. On this basis, the effects of the flight Mach number, altitude, angle of attack, sideslip angle on the acoustic pressure frequency spectrum and overall pressure level are analyzed to provide some engineering references for the cavity design in supersonic. © 2017, Nanjing Univ. of Aeronautics an Astronautics. All right reserved.

ISSN号：1004-4523

是否译文：否

发表时间：2017-06-01

合写作者：Wang, Fang-Li,Wang, Yi-Ding,Chen, Bin-Qi

通讯作者：童明波