Unsteady flow characteristics and noise reduction control methods of a geometrically complex weapons bay

WENG Zhe; WANG Xiao; LIU Chao; FU Jiawei; CHEN Tongyin; ZHAO Zhuolin; MAO Lei

doi:10.7638/kqdlxxb-2022.0030

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Unsteady flow characteristics and noise reduction control methods of a geometrically complex weapons bay

更新时间：2026-05-28

- Unsteady flow characteristics and noise reduction control methods of a geometrically complex weapons bay
- Vol. 40, Issue 3, Pages: 169-174(2022)
- 作者机构：
  
  中国航空工业集团公司沈阳飞机设计研究所,沈阳,110035
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0030
  CLC： V211.4
- Published：2022
- 稿件说明：
移动端阅览
瓮哲, 王霄, 刘超, 等. 内埋武器舱动态流动特性及降噪控制方法研究[J]. 空气动力学学报, 2022, 40(3): 169−174.

WENG Zhe, WANG Xiao, LIU Chao, et al. Unsteady flow characteristics and noise reduction control methods of a geometrically complex weapons bay[J]. 2022, 40(3): 169-174.
瓮哲, 王霄, 刘超, 等. 内埋武器舱动态流动特性及降噪控制方法研究[J]. 空气动力学学报, 2022, 40(3): 169−174. DOI： 10.7638/kqdlxxb-2022.0030

WENG Zhe, WANG Xiao, LIU Chao, et al. Unsteady flow characteristics and noise reduction control methods of a geometrically complex weapons bay[J]. 2022, 40(3): 169-174. DOI： 10.7638/kqdlxxb-2022.0030.

摘要

流动经过武器舱会产生诸如边界层分离、剪切层失稳、气动噪声等一系列复杂流动特征，进而可能对舱内设备和结构造成破坏。本文以近真实复杂内埋武器舱为研究对象，通过高精度数值仿真获取内埋武器舱动态流动特性；根据流场特性，分析武器舱内噪声产生机理，提出了前缘扰流片、导波管以及前缘吹气三种流动控制方案。通过高速风洞试验，系统分析了舱门开度、内埋武器挂载等因素对武器舱内噪声水平的影响，并且对不同扰流装置的降噪效果进行了测试分析。结果表明：内埋武器舱内流动以小尺度湍流结构为主；前舱在舱门小开度时总声压级较高，随开度增加后舱总声压级增大，舱门开到一定程度后，舱内总声压级分布基本一致。舱内挂载武器减弱流动对各壁面的拍击强度，使得舱内各壁面总声压级降低。三种控制方式均能够抬高剪切层，减弱武器舱内的能量注入，进而对武器舱内总声压级产生一定的降噪效果。在本文研究范围内，前缘扰流片的降噪效果最为显著，降噪幅值达5 dB。

Abstract

Flow past a weapon bay has a number of complex flow characteristics

such as the boundary layer separation

shear layer instabilities

acoustic noise

which may cause damage to the internal equipment or structure of the weapon bay itself. In this study

a complex weapon bay was developed to incorporate more realistic weapon bay features

and the unsteady flow characteristics inside the weapon bay were obtained using a high-precision numerical method. The noise generation mechanism was unveiled

based on which three types of flow control schemes

i.e. the leading-edge spoiler

the still-pipe

and the leading-edge air blowing

were proposed. Influence of the weapon-bay door opening angle and the embedded weapon on the noise level was systematically investigated using high-speed wind tunnel tests

and the noise reduction effects of different control devices were analyzed. The results show that

flow inside the weapon bay is dominated by small scale turbulent structures. The overall sound pressure level (OASPL) of the front cabin is relatively high when the door opening is small

and that of the rear cabin increases as the opening degree increases. After the door is opened to a certain extent

the OASPL distribution in the cabin remains the same. Embedding weapons lowers the OASPL in the weapon bay by weakening the slap intensity of the flow on each wall. All three control methods show significant reduction of OASPL by lifting up the shear layer and reducing the injected energy into the weapon bay. Based on the present study

the leading-edge spoiler is most effective in noise reduction

which can reduce the amplitude of OASPL by more than 5 dB.

关键词

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references

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. DOI:10.1016/j.paerosci.2010.11.002

ROSSITER J E. Wind-tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds[R ] . Aeronautical Research Council Reports Memoranda, ARC RM-3438, 1966. https://reports.aerade.cranfield.ac.uk/bitstream/handle/1826.2/4020/arc-rm-3438.pdf?sequence = 1isAllowed = y

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. DOI:10.1016/0022-460X(71)90105-2

CASPER K M, WAGNER J L, BERESH S J, et al. Complex geometry effects on cavity resonance[J]. AIAA Journal, 2015, 54(1): 320-330. DOI:10.2514/1.J054273

CATTAFESTA L N III, SONG Q, WILLIAMS D R, et al. Active control of flow-induced cavity oscillations[J]. Progress in Aerospace Sciences, 2008, 44(7-8): 479-502. DOI:10.1016/j.paerosci.2008.07.002

GAI S L, KLEINE H, NEELY A J. Supersonic flow over a shallow open rectangular cavity[J]. Journal of Aircraft, 2014, 52(2): 609-616. DOI:10.2514/1.C032781

SHAABAN M, MOHANY A. Passive control of flow-excited acoustic resonance in rectangular cavities using upstream mounted blocks[J]. Experiments in Fluids, 2015, 56(4): 1-12. DOI:10.1007/s00348-015-1908-8

DUDLEY J G, UKEILEY L. Passively controlled supersonic cavity flow using a spanwise cylinder[J]. Experiments in Fluids, 2014, 55(9): 1-22. DOI:10.1007/s00348-014-1810-9

ZHANG Y, ARORA N, SUN Y Y, et al. Suppression of cavity oscillations via three-dimensional steady blowing[C]//45th AIAA Fluid Dynamics Conference, Dallas, TX. Reston, Virginia: AIAA, AIAA 2015-3219, 2015. doi: 10.2514/6.2015-3219

GEORGE B, UKEILEY L S, CATTAFESTA L N, et al. Control of three-dimensional cavity flow using leading-edge slot blowing[C]//53rd AIAA Aerospace Sciences Meeting, Kissimmee, Florida. Reston, Virginia: AIAA, AIAA 2015-1059, 2015. doi: 10.2514/6.2015-1059

YUGULIS K, HANSFORD S, GREGORY J W, et al. Control of high subsonic cavity flow using plasma actuators[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine (Dallas/Ft. Worth Region), Texas. AIAA 2013-0679, 2013. doi: 10.2514/1.J052668

DE JONG A, BIJL H. Corner-type plasma actuators for cavity flow-induced noise control[J]. AIAA Journal, 2013, 52(1): 33-42. DOI:10.2514/1.J051815

YANG D G. Studies on aeroacoustic characteristics and noise suppressions for internal weapon bays[D]. Mianyang: China Aerodynamics Research and Development Center, 2010 (in Chinese).

WU J F. Investigation on aerodynamic characteristics of internal weapons bay system[D]. Mianyang, China: China Aerodynamics Research and Development Center, 2012 (in Chinese).

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): 121812. (in Chinese)

SHAW L, CLARK R, TALMADGE D. F-111 generic weapons bay acoustic environment[J]. Journal of Aircraft, 1988, 25(2): 147-153. DOI:10.2514/3.45555

WELTERLEN T. Weapons Bay flow field simulation[C]//18th Applied Aerodynamics Conference, Denver, CO, USA. Reston, Virigina: AIAA, AIAA 2000-3926, 2000. doi: 10.2514/6.2000-3926

PANICKAR M B, MURRAY N E, JANSEN B J Jr, et al. Reduction of noise generated by a half-open weapons bay[J]. Journal of Aircraft, 2013, 50(3): 716-724. DOI:10.2514/1.c031747

CHANDRASEKHAR K, CHRIS C, ROGER B, et al. Computational Modeling of Geometrically Complex Weapons Bays[C]//17th AIAA/CEAS Aeroacoustics Conference, Portland, Oregon, AIAA, AIAA 2011-2774, 2011. doi: 10.2514/6.2011-2774

LUO K Y, ZHE W, XIAO Z X, et al. Improved delayed detached-eddy simulations of sawtooth spoiler control before supersonic cavity[J]. International Journal of Heat and Fluid Flow, 2017, 63: 172-189. DOI:10.1016/j.ijheatfluidflow.2017.01.012

ZHANG Y, SUN Y Y, ARORA N, et al. Suppression of cavity flow oscillations via three-dimensional steady blowing[J]. AIAA Journal, 2018, 57(1): 90-105. DOI:10.2514/1.J057012

ZHUANG N, ALVI F S, ALKISLAR M B, et al. Supersonic cavity flows and their control[J]. AIAA Journal, 2006, 44(9): 2118-2128. DOI:10.2514/1.14879

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