基于金属丝网的超声速空腔流动控制

Supersonic cavity flow control based on wire mesh

摘要

飞行器内埋式弹舱是一种典型的空腔结构，所激发的气动噪声会对飞行器机体结构与舱内设备造成不利影响，有效的流动控制方法抑制空腔气动噪声对提升飞行器综合性能具有重要意义本文提出基于金属丝网的空腔流动被动控制方法，使用改进延迟分离涡模拟（IDDES，improved delayed detached eddy simulation）方法对长深比为5的M219空腔标模展开超声速工况数值模拟计算，分析对比不同孔隙率金属丝网与平板扰流板的降噪效果，利用谱本征正交分解（SPOD，spectral proper orthogonal decomposition）方法深入分析流场结构与噪声机理结果表明，金属丝网允许部分气体流过，同时抬升另一部分气流，这种独特的分流机制既能削弱剪切层失稳噪声，又可抑制后缘碰撞噪声，实现了对两种噪声源的同时控制其中后缘碰撞噪声对应低阶Rossiter模态，剪切层失稳噪声对应高阶Rossiter模态当金属丝网孔隙率为0.30时，取得了优秀的降噪性能与平板扰流板相比，金属丝网避免了额外噪声源的引入，展现出更好的综合降噪性能本研究为空腔流动控制研究提供了新的被动控制方法与理论支持。

Abstract

The internal weapon bay of an aircraft is a typical cavity structure, and the aerodynamic noise it excites adversely affects the airframe structure and the equipment inside the bay. Proposing effective flow control methods to suppress cavity aerodynamic noise is therefore of great significance for improving the overall performance of aircraft. This paper proposes a passive cavity flow control method based on wire mesh. Numerical simulations under supersonic conditions are carried out for the M219 cavity calibration model with a length-to-depth ratio of 5 by using the improved delayed detached eddy simulation (IDDES) method. The noise reduction effects of wire meshes with different porosities are analyzed and compared with those of a flat-plate spoiler. The flow field structures and noise mechanisms are further analyzed by using the spectral proper orthogonal decomposition (SPOD) method. The results show that the wire mesh allows part of the air to flow through while lifting the other part of the flow. This unique flow-splitting mechanism can both weaken the shear layer instability noise and suppress the trailing-edge impingement noise, thus achieving simultaneous control of the two noise sources. The trailing-edge impingement noise corresponds to the low-order Rossiter modes, whereas the shear layer instability noise corresponds to the high-order Rossiter modes. When the porosity of the wire mesh is 0.30, excellent noise reduction performance is achieved. Compared with the flat-plate spoiler, the wire mesh avoids the introduction of additional noise sources and exhibits better overall noise reduction performance. This study provides a new passive control method and theoretical support for the study of cavity flow control.

关键词

空腔流动 / 气动噪声 / 谱本征正交分解（SPOD） / 金属丝网 / 流动控制

参考文献

[1] Saddington A J, Knowles K, Thangamani V. Scale effects on the performance of sawtooth spoilers in transonic rectangular cavity flow[J]. Experiments in Fluids, 2015, 57(1): 2.

[2] Lawson S J, Barakos G N. Review of numerical simulations for high-speed, turbulent cavity flows[J]. Progress in Aerospace Sciences, 2011, 47(3): 186-216.

[3] Krishnamurty K. Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces: NACA TN-3487[R]. Washington, D. C.: National Advisory Committee for Aeronautics, 1955.

[4] Karamcheti K. Sound radiation from surface cutouts in high speed flow[D]. Pasadena: California Institute of Technology, 1956.

[5] Roshko A. Some measurements of flow in a rectangular cutout: NACA-TN-3488[R]. Washington, D.C.: National Advisory Committee for Aeronautics, 1955.

[6] Rossiter J E. Wind-tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds: ARC R M 3438[R]. London, UK: Aeronautical Research Council, 1964.

[7] Shaw L, Clark R, Talmadge D. F-111 generic weapons bay acoustic environment[J]. Journal of Aircraft, 1988, 25(2): 147-153.

[8] Lee S C, Lua K B. Flow control devices for aeroacoustic noise suppression in cavity flow[J]. Journal of Aircraft, 2025, 62(5): 1302-1313.

[9] Aydin M, Göktekin K T, Karaaslan R, et al. High fidelity CFD simulation of cavity flow and its active flow control using steady mass flow injection[C]// AIAA SCITECH 2023 Forum, January 23-27, 2023, National Harbor, MD & Online. Reston, Virginia: AIAA, 2023: 0977.

[10] Kaba R, Yildiz S, Zafer B, et al. Aeroacoustic optimization of unsteady transonic cavity flow using a Bayesian approach[J]. CEAS Aeronautical Journal, 2026, 17(2): 567-593.

[11] Cui Pengcheng, Zhou Guiyu, Zhang Yaobing, et al. Improved delayed detached-eddy investigations on the flow control of the leading-edge flat spoiler of the cavity in the low-aspect-ratio aircraft[J]. Aerospace, 2022, 9(9): 526.

[12] 余培汛, 白俊强, 郭博智, 等. 剪切层形态对开式空腔气动噪声的抑制[J]. 振动与冲击, 2015, 34(1): 156-164.

[13] Luo Kunyu, Zhu Wenqing, Xiao Zhixiang, et al. Investigation of spectral characteristics by passive control methods past a supersonic cavity[J]. AIAA Journal, 2018, 56(7): 2669-2686.

[14] Zhang Qinghe, Feng Shuyang, Zhou Fangqi, et al. Experimental investigation of passive control for cavity noise in high-speed flow using sawtooth spoiler[J]. Applied Acoustics, 2023, 211: 109567.

[15] Ukeiley L S, Ponton M K, Seiner J M, et al. Suppression of pressure loads in cavity flows[J]. AIAA Journal, 2004, 42(1): 70-79.

[16] Zhu Wenqing, Xiao Zhixiang, Fu Song. Numerical modeling screen for flow and noise control around tandem cylinders[J]. AIAA Journal, 2020, 58(6): 2504-2516.

[17] Terracol M, Manoha E, Manueco L, et al. Numerical simulations of a landing gear with flow through fairings for noise mitigation[C]// AIAA AVIATION 2023 Forum. San Diego, CA and Online. AIAA, 2023: AIAA2023-4173.

[18] Yalcin O, Ozyoruk Y. Delayed detached-eddy simulations of transonic cavity noise[C]// AIAA Aviation 2021 Forum. Virtual Event. AIAA, 2021: AIAA2021-2165.

[19] Mancini S, Kolb A, Gonzalez-Martino I, et al. Very-large eddy simulations of the M219 cavity at high-subsonic and supersonic conditions[C]// AIAA Scitech 2019 Forum, January 7-11, 2019, San Diego, California. Reston, Virginia: AIAA, 2019: 1833.

[20] Luo Kunyu, Xiao Zhixiang. Improved delayed detached-eddy simulation of transonic and supersonic cavity flows[C]// Progress in Hybrid RANS-LES Modelling. Cham: Springer International Publishing, 2015: 163-174.

[21] Henshaw M J C. M219 cavity case[R]//Verification and Validation Data for Computational Unsteady Aerodynamics: RTO-TR-26. NATO Research and Technology Organization, 2000.

[22] Roach P E. The generation of nearly isotropic turbulence by means of grids[J]. International Journal of Heat and Fluid Flow, 1987, 8(2): 82-92.

[23] Li Shuai, Davidson L, Peng S H. Numerical modeling of a wire mesh for aerodynamic noise reduction[J]. Physics of Fluids, 2023, 35: 015103.

[24] Okolo P N, Zhao Kun, Kennedy J, et al. Numerical modeling of wire screens for flow and noise control[C]// 23rd AIAA/CEAS Aeroacoustics Conference. Denver, Colorado. AIAA, 2017: AIAA2017-3700.

[25] Méry F, Sebbane D. Aerodynamic characterisation of porous fairings: pressure drop and laser Doppler velocimetry measurements[J]. Scientific Data, 2023, 10: 39

[26] Li Shuai, Davidson L, Peng S H, et al. On the mitigation of landing gear noise using a solid fairing and a dense wire mesh[J]. Aerospace Science and Technology, 2024, 153: 109465.

[27] Heller H H, Bliss D B. Aerodynamically induced pressure oscillations in cavities: physical mechanisms and suppression concepts: AFFDL - TR-74-133[R]. Wright-Patterson Air Force Base, OH: Air Force Flight Dynamics Laboratory, 1975.

[28] Heller H H, Holmes D G, Covert E E. Flow-induced pressure oscillations in shallow cavities[J]. Journal of Sound and Vibration, 1971, 18(4): 545-553.

[29] Raman G, Envia E, Bencic T. Tone noise and nearfield pressure produced by jet-cavity interaction[C]// 37th Aerospace Sciences Meeting and Exhibit, January 11-14, 1999, Reno, NV. Reston, Virginia: AIAA, 1999: 604.

[30] Towne A, Schmidt O T, Colonius T. Spectral proper orthogonal decomposition and its relationship to dynamic mode decomposition and resolvent analysis[J]. Journal of Fluid Mechanics, 2018, 847: 821-867.

基金资助

国家自然科学基金项目(52372362)

陕西省自然科学基础研究计划(2025JC-JCQN-071)

浙江省自然科学基金项目(LR25A020001)