高马赫数内埋武器舱被动流动控制措施

张培红; 陈洪杨; 张杰; 罗磊; 周方奇; 贾洪印

doi:10.13700/j.bh.1001-5965.2021.0790

高马赫数内埋武器舱被动流动控制措施

doi: 10.13700/j.bh.1001-5965.2021.0790

1.
中国空气动力研究与发展中心计算空气动力研究所，绵阳 621000
2.
中国空气动力研究与发展中心高速空气动力研究所，绵阳 621002

基金项目: 国家数值风洞工程项目

详细信息

通讯作者:
E-mail：fqzhou20@126.com

中图分类号: V221⁺.3；TB553
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出版历程
- 收稿日期: 2021-12-28
- 录用日期: 2022-03-20
- 网络出版日期: 2022-05-10
- 整期出版日期: 2023-11-30

Passive flow control for weapon bay at high Mach number

1.
Computational Aerodynamic Institute of China Aerodynamics Research and Development Center，Mianyang 621000，China
2.
High Speed Aerodynamic Institute of China Aerodynamics Research and Development Center，Mianyang 621002，China

Funds: National Numerical Windtunnel Project

More Information

Corresponding author: E-mail：fqzhou20@126.com

摘要

摘要:
高马赫数(Ma>2)武器舱剪切层更强、更稳定，其噪声产生机制与通常的亚、跨、超声速武器舱流动不同，导致用来抑制空腔噪声的流动控制措施也不同。分别采用数值模拟和风洞试验2种手段，研究了圆柱形机身和马赫数对空腔流动特性的影响，以及前缘锯齿、前缘立柱、前缘横柱、前缘挡板等不同被动流动控制措施对高马赫数武器舱声压级特性的影响，为高马赫数武器舱的流动控制措施设计和研究提供参考。研究表明：圆柱形机身对空腔底部的压力分布会产生影响，压力分布的不均匀性增大，后壁附近的压力峰值增大；对通常的亚、跨、超声速武器舱流动较为有效的被动流动控制措施，对高马赫数空腔流动效果不明显，甚至会加大武器舱内的噪声等级，需要开展更为深入的研究，以设计更为有效的流动控制措施。
- 武器舱 /
- 数值模拟 /
- 风洞试验 /
- 流动控制 /
- 声压级
Abstract:
The noise generation mechanism of weapon bays at a high Mach number (Ma>2) is different from that of the subsonic, transonic, and supersonic weapon bay flow because of the stronger and more stable shear layer. This discrepancy may also lead to different flow control measures for cavity noise suppression. Using numerical simulations and wind tunnel tests, this study examines the effects of the cylindrical fuselage and Mach number on cavity flow characteristics, and of different passive flow control measures such as leading edge serrations, leading edge columns, leading edge transverse columns and leading edge baffles on the sound pressure level of a weapon bay at a high Mach number. This study provides a reference for the design and research of flow control measures for a high Mach number weapon bay. The results show that the cylindrical fuselage has an impact on the pressure distribution at the cavity bottom, that the unevenness of the pressure distribution increases, and that the pressure peak near the rear wall increases. The passive flow control measures, which are more effective for the subsonic, transonic and supersonic weapon bay flow, are not effective for the high Mach number cavity flow, and even increase the noise level in the weapon bay. Further research is needed to design more effective flow control measures.
- weapon bay /
- numerical simulation /
- wind tunnel test /
- flow control /
- sound pressure level

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图 1 风洞试验模型示意图

Figure 1. Model of wind tunnel test

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图 2 风洞试验模型尺寸示意图

Figure 2. Sketch of wind tunnel test model

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图 3 FL-32风洞结构轮廓示意图

Figure 3. Structure schematic of FL-32 wind tunnel

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图 4 数值模拟与风洞试验声压级结果比较

Figure 4. Comparison of SPL results of CFD and wind tunnel test

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图 5 数值模拟与文献[31]试验声压级结果比较

Figure 5. Comparison of SPL results of CFD and Ref. [31] experiment

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图 6 2种简化模型外形示意图

Figure 6. Schematic of two simplified models

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图 7 2种简化模型表面压力分布比较

Figure 7. Comparison of surface pressure distribution on wall of two simplified models

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图 8 2种简化模型对称面表面压力分布比较

Figure 8. Comparison of pressure distribution on symmetry plane of two simplified models

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图 9 2种简化模型对称面总压恢复0.99等值线比较

Figure 9. Comparison of two simplified models with total pressure recovery of 0.99 on symmetry plane

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图 10 不同流动控制措施试验模型

Figure 10. Test model with different flow control measures

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图 11 试验模型在风洞中的安装情况

Figure 11. Installation of test model in wind tunnel

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图 12 流动控制对武器舱内静压分布的影响

Figure 12. Influence of flow control on static pressure distribution in weapon bay

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图 13 流动控制对武器舱内声压级的影响

Figure 13. Influence of flow control on sound pressure level distribution in weapon bay

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表 1 数值模拟得到的监控点K不同模态时声压级频率、幅值与风洞试验值^[31]比较

Table 1. Comparison between frequency and amplitude values of SPL at different modes for monitoring point K obtained from CFD and experimental results^[31]

模态	声压级频率/Hz		频率误差/%	声压级幅值/dB		幅值误差/dB
模态	文献[31]试验值	数值模拟值	频率误差/%	文献[31]试验值	数值模拟值	幅值误差/dB
1阶	287	275	−4.18	132.5	135.6	3.1
2阶	695	689	−0.86	132.1	135.8	3.7
3阶	1152	1195	3.73	132.8	138	5.2
4阶	1527	1516	−0.72	131	134.7	3.7

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