空腔噪声的马赫数敏感性研究

刘俊; 蔡晋生; 周方奇

doi:10.11729/syltlx20190079

空腔噪声的马赫数敏感性研究

doi: 10.11729/syltlx20190079

刘俊^{1, 2,},
蔡晋生^1, ,,
周方奇²

1.
西北工业大学航空学院, 西安 710072
2.
中国空气动力研究与发展中心空气动力学国家重点实验室, 四川绵阳 621000

基金项目:

空气动力学国家重点实验室研究基金 SKLA20170304

详细信息

作者简介:
刘俊(1986-), 男, 湖南浏阳人, 博士研究生, 工程师。研究方向:非定常空气动力学及数值流场可视化。通信地址:陕西省西安市碑林区西北工业大学航空学院。E-mail:ljun05@163.com

通讯作者:
蔡晋生，E-mail: caijsh@nwpu.edu.cn

中图分类号: V211;TB84
计量
- 文章访问数: 192
- HTML全文浏览量: 124
- PDF下载量: 15
- 被引次数: 0
出版历程
- 收稿日期: 2019-06-25
- 修回日期: 2019-09-17
- 刊出日期: 2020-06-25

Mach number sensitivity analysis of cavity noise

LIU Jun^{1, 2
,},
CAI Jinsheng^{1
, ,},
ZHOU Fangqi²

1.
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
2.
State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 敏感度分析在评估参数的重要程度以及计算不确定度方面具有重要作用。通过风洞试验开展了亚跨超声速下的空腔噪声马赫数敏感性研究。亚跨声速下，通过调节调压阀的开度改变马赫数，马赫数名义增量为0.010。超声速下，通过改变模型迎角实现马赫数的连续变化，迎角增量为1°。利用总压耙测量空腔入口马赫数。结果表明：空腔后部测点脉动压力系数在亚跨声速下随着马赫数的增加而增加，而在超声速下随着马赫数的增加而减小。跨声速下，脉动压力系数对马赫数的敏感性导数最大。不考虑模态切换的情况下，不同速域的主导声模态St对马赫数的敏感性导数均为负数。主导声模态谱峰在亚声速下随着马赫数的增加而增加，而在超声速下随着马赫数的增加而降低。敏感度研究结果不仅可用于内埋武器舱气动噪声载荷的不确定度评估，也有助于更好地认识空腔噪声特性。
- 空腔流动 /
- 噪声 /
- 马赫数 /
- 敏感性分析 /
- 风洞试验
Abstract: Sensitivity analysis plays an important role in assessing the importance of parameters and calculating the uncertainty. Mach number sensitivity analysis of cavity noise at subsonic, transonic and supersonic speed has been investigated by wind tunnel experiments in this study. At subsonic speed, the Mach number is changed by adjusting the opening of the valve, and the nominal increment of the Mach number is 0.01.At supersonic speed, the continuous change of the Mach number is achieved by changing the angle of attack of the model, and the increment of angle of attack is 1 degree. The experimental results show that the fluctuating pressure coefficient at the rear of the cavity increases with the increase of the Mach number at the subsonic speed, while decreases with the increase of the Mach number at the supersonic speed. At transonic speed, the fluctuating pressure coefficient has the largest sensitivity derivative to the Mach number. In the case of modal switching, the derivative of St to Mach number for the dominant acoustic mode is negative. The peak value of the dominant acoustic mode's power spectral density increases with the increase of Mach number at subsonic speed, while decreases at supersonic speed. The obtained sensitivity results can be used not only for the uncertainty assessment of the aerodynamic noise load in the embedded weapon bay, but also for a better understanding of the cavity noise characteristics.
- cavity flows /
- noise /
- Mach number /
- sensitivity analysis /
- wind-tunnel experiments

HTML全文

图 1 C201空腔模型

Figure 1. C201 cavity model

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图 2 脉动压力传感器安装位置

Figure 2. Positions of fluctuating pressure sensors

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图 3 边界层总压耙

Figure 3. Total pressure probes in boundary layer

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图 4 脉动压力系数随马赫数的变化曲线

Figure 4. Curves of fluctuating pressure coefficients vs Mach numbers

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图 5 亚跨超声速下空腔脉动压力系数对马赫数的敏感性导数

Figure 5. Sensitivity of fluctuating pressure coefficients to Mach numbers in subsonic, transonic and supersonic cavity flows

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图 6 亚跨超声速下不同马赫数的脉动压力功率谱

Figure 6. Power spectrum of dynamic pressure for different Mach numbers at subsonic, transonic and supersonic speed

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图 7 St随马赫数的变化曲线

Figure 7. Curves of St number with Mach number

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图 8 主导声模态谱峰随马赫数的变化曲线

Figure 8. Curves of peak values of normalized pressure spectral density with Mach numbers

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表 1 马赫数测量结果

Table 1. Mach numbers measured by boundary layer probes

	Ma₁	Ma₂	Ma₃	Ma₄
亚声速	0.5785	0.5899	0.5992	0.6087
跨声速	0.8802	0.8905	0.9000	0.9106
超声速	1.9740	2.0102	2.0471	2.0843

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表 2 主导模态St对马赫数的敏感性导数

Table 2. Sensitivity of St numbers to Mach numbers

	∂St/∂Ma
亚声速(Ma=0.60)	-0.794
跨声速(Ma=0.90)	-1.011(Mode 1), -0.889(Mode 2)
超声速(Ma=2.00)	-0.369

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表 3 主导声模态谱峰对马赫数的敏感性导数

Table 3. Sensitivity of peak value of normalized pressure spectral density to Mach numbers

	Mode 1	Mode 2	Mode 3	Mode 4	Mode 5
亚声速	—	0.252	-0.092	0.308	—
跨声速	-9.467	16.449	-0.844	—	—
超声速	-0.014	-0.020	-0.008	-0.029	-1.129

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参考文献(25)

[1]	董雪, 张德平.基于极限学习机的武器装备作战效能全局敏感性分析[J].计算机与现代化, 2018(5):86-92. doi: 10.3969/j.issn.1006-2475.2018.05.018 DONG X, ZHANG D P. Global sensitivity analysis and optimization of submarine combat effectiveness based on extreme learning machine[J]. Computer and Modernization, 2018(5):86-92. doi: 10.3969/j.issn.1006-2475.2018.05.018
[2]	周智超.面向武器装备系统效能的敏感性分析[J].火力与指挥控制, 2013, 38(2):98-102. doi: 10.3969/j.issn.1002-0640.2013.02.026 ZHOU Z C. Sensitivity analysis of oriented to system effectiveness of weapons and equipment[J]. Fire Control & Command Control, 2013, 38(2):98-102. doi: 10.3969/j.issn.1002-0640.2013.02.026
[3]	李永乐, 苏茂材, 王士刚, 等.大跨度钢桁梁铁路斜拉桥刚度参数敏感性分析[J].振动与冲击, 2015, 34(2):166-170. http://d.old.wanfangdata.com.cn/Periodical/zdycj201502030 LI Y L, SU M C, WANG S G, et al. Sensitivity of structural stiffness parameters of long-span steel truss cable-stayed railway bridge[J]. Journal of Vibration and Shock, 2015, 34(2):166-170. http://d.old.wanfangdata.com.cn/Periodical/zdycj201502030
[4]	李加武, 方成, 侯利明, 等.大跨径桥梁静风稳定参数的敏感性分析[J].振动与冲击, 2014, 33(4):124-130. doi: 10.3969/j.issn.1000-3835.2014.04.023 LI J W, FANG C, HOU L M, et al. Sensitivity analysis for aerostatic stability parameter of a long-span bridge[J]. Journal of Vibration and Shock, 2014, 33(4):124-130. doi: 10.3969/j.issn.1000-3835.2014.04.023
[5]	李宪文, 刘锦, 郭钢, 等.致密砂岩储层渗吸数学模型及应用研究[J].特种油气藏, 2017, 24(6):79-83. doi: 10.3969/j.issn.1006-6535.2017.06.015 LI X W, LIU J, GUO G, et al. Mathematical model of imbibition and its application in tight sandstone reservoir[J]. Special Oil & Gas Reservoirs, 2017, 24(6):79-83. doi: 10.3969/j.issn.1006-6535.2017.06.015
[6]	杨旭东, 乔志德, 朱兵.升力系数不变时跨音速机翼阻力优化设计[J].计算物理, 2003, 20(3):233-238. doi: 10.3969/j.issn.1001-246X.2003.03.009 YANG X D, QIAO Z D, ZHU B. Optimization design of transonic wings with drag reduction and constant lift coefficients[J]. Chinese Journal of Computation Physics, 2003, 20(3):233-238. doi: 10.3969/j.issn.1001-246X.2003.03.009
[7]	江奕廷, 白俊强, 孙智伟.基于参数敏感性分析的反设计方法[J].航空计算技术, 2012, 42(6):65-69. doi: 10.3969/j.issn.1671-654X.2012.06.017 JIANG Y T, BAI J Q, SUN Z W. Inverse airfoil design based on sensitive analysis of parameterized methods[J]. Aeronautical Computing Technique, 2012, 42(6):65-69. doi: 10.3969/j.issn.1671-654X.2012.06.017
[8]	罗鹏程, 傅攀峰.武器装备敏感性分析方法综述[J].计算机工程与设计, 2008, 29(21):5546-5549. http://d.old.wanfangdata.com.cn/Periodical/jsjgcysj200821042 LUO P C, FU P F. Review on weapons and equipment sensitivity analysis methods[J]. Computer Engineering and Design, 2008, 29(21):5546-5549. http://d.old.wanfangdata.com.cn/Periodical/jsjgcysj200821042
[9]	金镭, 张曙光, 孙金标.现代战斗机空战能力评估及敏感性分析[J].北京航空航天大学学报, 2009, 35(1):82-86. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=bjhkhtdxxb200901020 JIN L, ZHANG S G, SUN J B. Air-combat ability and sensitivity analysis of modern fighter aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(1):82-86. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=bjhkhtdxxb200901020
[10]	唐冕, 陈政清.大跨径自锚式悬索桥气动参数的敏感性分析[J].湖南科技大学学报(自然科学版), 2008, 23(1):55-59. http://d.old.wanfangdata.com.cn/Periodical/xtkyxyxb200801013 TANG M, CHEN Z Q. Sensitivity analysis of aerodynamic parameter for long-span self-anchored suspension bridges[J]. Journal of Hunan University of Science & Technology, 2008, 23(1):55-59. http://d.old.wanfangdata.com.cn/Periodical/xtkyxyxb200801013
[11]	徐林程, 王刚, 武洁, 等.翼型模型几何误差对气动性能影响的自动微分分析方法[J].空气动力学学报, 2014, 32(4):551-556. doi: 10.7638/kqdlxxb-2013.0097 XU L C, WANG G, WU J, et al. An automatic differentiation method for uncertainty analysis due to airfoil configuration variation[J]. Acta Aerodynamica Sinica, 2014, 32(4):551-556. doi: 10.7638/kqdlxxb-2013.0097
[12]	徐林程, 王刚, 武洁, 等.翼型风洞试验中不确定性分析的自动微分方法[J].航空学报, 2014, 35(8):2102-2111. http://d.old.wanfangdata.com.cn/Periodical/hkxb201408003 XU L C, WANG G, WU J, et al. Uncertainty analysis of airfoil wind tunnel tests with automatic differentiation[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(8):2102-2111. http://d.old.wanfangdata.com.cn/Periodical/hkxb201408003
[13]	ALBRING T A, SAGEBAUM M, GAUGER N R. Efficient aerodynamic design using the discreteadjoint method in SU2[R]. AIAA-2016-3518, 2016.
[14]	YANG G D, RONCH A D. Aerodynamic shape optimisation of benchmark problems using SU2[R]. AIAA-2018-0412, 2018.
[15]	LIU H K, YAN C, ZHAO Y T, et al. Uncertainty and sensitivity analysis of flow parameters on aerodynamics of a hypersonic inlet[J].Acta Astronautica, 2018, 151:703-716. doi: 10.1016/j.actaastro.2018.07.011
[16]	PLENTOVICH E B. Three-dimensional cavity flow fields at subsonic and transonic speeds[R]. NASA-TM-4209, 1990.
[17]	THANGAMANI V, KNOWLES K, SADDINGTON A J. The effects of scaling on high subsonic cavity flow oscillations and control[R]. AIAA-2012-2052, 2012.
[18]	MERRICK J D. Influence of Mach number and dynamic pressure on cavity tones and freedrop trajectories[D]. Ohio: Air Force Air University, 2014.
[19]	王显圣, 杨党国, 刘俊, 等.弹性空腔流致噪声/结构振动特性试验[J].航空学报, 2017, 38(7):182-191. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201707015 WANG X S, YANG D G, LIU J, et al. Test on interactions between aeroacoustic noise and structural vibration in elastic cavity flow[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(7):182-191. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201707015
[20]	周方奇, 杨党国, 王显圣, 等.前缘直板扰流对高速空腔的降噪效果分析[J].航空学报, 2018, 39(4):133-143. http://d.old.wanfangdata.com.cn/Periodical/hkxb201804011 ZHOU F Q, YANG D G, WANG X S, et al. Effect of leading edge plate on high speed cavity noise control[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(4):133-143. http://d.old.wanfangdata.com.cn/Periodical/hkxb201804011
[21]	HANKEY W L, SHANG J S. Analyses of pressure oscillations in an open cavity[J]. AIAA Journal, 1980, 18(8):892-898. doi: 10.2514/3.50831
[22]	熊红亮, 袁格, 李潜, 等.可压缩自由剪切层纹影试验研究[J].流体力学实验与测量, 2003, 17(2):74-77, 83. doi: 10.3969/j.issn.1672-9897.2003.02.015 XIONG H L, YUAN G, LI Q, et al. Flow visualization about a compressible shear flow[J]. Experiments and Measurements in Fluid Mechanics, 2003, 17(2):74-77, 83. doi: 10.3969/j.issn.1672-9897.2003.02.015
[23]	ROSSITER J E.Wind-tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds: 64037[R]. RAE Technical Report No.64037, 1964.
[24]	CHANDRA B U, CHAKRAVARTHY S R. Experimental investigation of cavity-induced acoustic oscillations in confined supersonic flow[J]. Journal of Fluids Engineering, 2005, 127(4):761-769. doi: 10.1115/1.1949642
[25]	WANG Y C, TAN L, WANG B B, et al. Numerical investigation on frequency jump of flow over a cavity using large eddy simulation[J]. Journal of Fluids Engineering, 2015, 137(8):081203. doi: 10.1115/1.4030002