Page 44 - 《应用声学》2022年第6期

890 2022 年 11 月

ᮕ฾ϙ ࢺц1 ࢺц2 ࢺц3 ࢺц4
តᰎϙ ࢺц1 ࢺц2 ࢺц3 ࢺц4

5 dB 5 dB
Ҫဋ៨/dB Ҫဋ៨/dB

20 200 2000 20 200 2000
ᮠဋ/Hz ᮠဋ/Hz
(a) 2Ղ฾ག (b) 8Ղ฾ག
图 11 试验值和优化后的预测结果对比
Fig. 11 Comparison of test value and optimized prediction result
表 4 最小二乘法求 A、B (基于 8 号测点) [6] Howe M S. Sound generation in a fluid with rigid
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Table 4 Calculating parameter A and B
tions. Cambridge: Cambridge University Press, 1998:
by least square method (based on Point 8)
164–166.
[7] Goody M. Empirical spectral model of surface pressure
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本文对某型民机巡航阶段的机体表面压力脉 AIAA/CEAS Aeroacoustics Conference and Exhibit,
1999: 1964.
动进行了分析。机身表面的压力脉动主要由湍流边 [10] Rackl R G, Weston A. Modeling of turbulent boundary
界层噪声贡献，在前后机身区域，发动机噪声完全淹 layer surface pressure fluctuation auto and cross spectra:
没在湍流边界层噪声中。湍流边界层噪声的幅值与 verification and adjustments based on tu-144ll data[M].
National Aeronautics and Space Administration, Langley
动压呈正相关。边界层厚度对湍流边界层噪声的影 Research Center, 2005.
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