The static and fluctuating pressure characteristics of cavity flow in a weapon bay were tested in a high speed wind tunnel, and the flow control method with perforated plate or injection which was added to the leading edge of the cavity was studied with changing parameters. The test Mach number 0.75, cavity length 300 mm, length-to-depth ratio 3, and width-to-depth ratio 1. Experimental results showed that on the ceiling of the cavity and along the flow direction, the pressure distribution is relatively uniform. The spectra for different monitor points showed the same modal characteristics, which is typical of open cavity flow and is barely affected by the change of angle of attack within a certain range. At the typical flight angle of attack, the flow control method of the leading-edge perforated plate can improve the pressure distribution along the flow direction and reduce the fluctuating pressure in the cavity. The installation height and the span-wise length of the perforated plate have a significant impact on the flow control effect. Within certain range, the combination of large installation height and small span-wise length has a better flow control effect on the perforated plate, which can also work steadily at different angles of attack. At the typical flight angle of attack, the flow control method of leading-edge injection can also improve the pressure distribution along the flow direction and reduce the fluctuating pressure in the cavity. The jet slot width and the jet flow rate have a significant impact on the flow control effect. Within certain range, the combination of small span-wise width and large jet flow rate has a better flow control effect on the leading-edge injection, which can also work steadily at different angles of attack.
XIE Lu
,
ZHANG Yanjun
,
HOU Yinzhu
,
LIU Wei
,
LEI Wutao
. Cavity flow pressure characteristics and flow control methods of subsonic weapon bay[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020
, 41(11)
: 123961
-123961
.
DOI: 10.7527/S1000-6893.2020.23961
[1] SHAW L, BARTEL H, MCAVOY J. Acoustic environment in large enclosures with a small opening exposed to flow[J]. Journal of Aircraft, 1983, 20(3):250-256.
[2] STALLINGS R, WILCOX F. Experimental cavity pressure distributions at supersonic speeds:NASA TR TP-2683[R]. Washington,D.C.:NASA Langley Research Center, 1987.
[3] PLENTOVICH E B, STALLINGS R L, TRACY M B. Experimental cavity pressure measurements at subsonic and transonic speeds:NASA TP 3358[R]. Washington, D.C.:NASA, 1993.
[4] TRACY M B, PLENTOVICH E B. Characterization of cavity flow fields using pressure data obtained in the Langley 0.3-meter transonic cryogenic tunnel:NASA TM 4436[R]. Washington, D.C.:NASA, 1993.
[5] MICHAEL J S. A numerical study of the effect of frequency of pulsed flow control applied to a rectangular cavity in supersonic crossflow[D]. Cincinnati:University of Cincinnati, 2005.
[6] CLARK R L. Evaluation of F-111 weapon bay aero-acoustic and weapon separation improvement techniques:AFFDL-TR-79-3003[R]. 1979.
[7] SHAW L, CLARK R, TALMADGE D. F-lll generic weapons bay acoustic environment[J]. Journal of Aircraft, 1988, 25(2):147-153.
[8] GROVE J, SHAW L,LEUGERS J, et al. USAF/RAAF F-111 flight test with active separation control[C]//41 st Aerospace Sciences Meeting and Exhibit. Reston:AIAA, 2003.
[9] TIPTON A G,SHAW L L. Weapon bay cavity noise environments data correlation and prediction for the B-1 aircraft:AFWAL-TR-0-3060[R]. Los Angeles:Rockwell International Corporation, 1980.
[10] CENKO A, DESLANDES R, DILLENIUS M, et al. Unsteady weapon bay aerodynamics-Urban legend or flight clearance nightmare[C]//46th AIAA Aerospace Sciences Meeting and Exhibit. Reston:AIAA, 2008.
[11] AHMAD D. Vakili and christian gauthiert. control of cavity flow by upstream mass-injection[J]. Journal of Aircraft, 1994, 31(1):169-174.
[12] SHAW L L. High speed application of active flow control for cavity acoustics[C]//6th AIAA/CEAS Aeroacoustics Conference and Exhibit. Reston:AIAA, 2000.
[13] SHAW L L. Actuator optimization for active flow control of cavity acoustics[C]//7th AIAA/CEAS Aeroacoustics Conference. Reston:AIAA, 2001.
[14] LAWSON S J, BARAKOS G N. Assessment of passive flow control for transonic cavity flow using detached-eddy simulation[J]. Journal of Aircraft, 2009, 46(3):1009-1029.
[15] SADDINGTON A J, THANGAMANI V, KNOWLES K. Comparison of passive flow control methods for a cavity in transonic flow[J]. Journal of Aircraft, 2016, 53(5):1439-1447.
[16] ZACHARY P, MARK F R, RUDY J, et al. Flight-test experiments on cavity flow in an SUU-41 pod[J]. Journal of Aircraft, 2017, 54(5):1814-1824.
[17] DANIEL P, MARK F R, RYAN S, et al. Flight test of passive flow control for acoustic suppression[C]//AIAA Aviation 2019 Forum. Reston:AIAA, 2019.
[18] 冯强,崔晓春. 飞翼布局飞机武器舱综合流动控制技术[J]. 航空学报, 2012,33(5):781-787. FENG Q, CUI X C. Study on integrated flow control for weapons bay of flying wing configuration aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(5):781-787(in Chinese).
[19] 宋文成,李玉军,冯强.武器舱气动噪声主动流动控制技术风洞试验研究[J].空气动力学学报,2016,34(1):33-39. SONG W C, LI Y J, FENG Q. Wind tunnel test research on weapon bay cavity active flow control for acoustic[J]. Acta Aerodynamica Sinica, 2016, 34(1):33-39(in Chinese).
[20] 杨党国,范召林,李建强,等. 后壁倒角对空腔噪声的抑制效果[J]. 实验流体力学,2010, 24(5):22-25. YANG D G, FAN Z L, LI J Q, et al. Suppression effects of rear-face angle of cavity on its aerodynamics noise[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(5):22-25(in Chinese).
[21] 吴继飞,徐来武,范召林,等. 开式空腔气动声学特性及其流动控制方法[J]. 航空学报,2015, 36(7):2155-2165. WU J F, XU L W, FAN Z L, et al. Aeroacoustic characteristics and flow control method of open cavity flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(7):2155-2165(in Chinese).
[22] CATTAFESTA L N, WILLIAMS D R, ROWLEY C W, et al. Review of active control of flow-induced cavity resonance:AIAA-2003-3567[R]. Reston:AIAA, 2003.
[23] ROSSITER J E. Wind-tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds[R]. London:Aeronautical Research Council Reports and Memoranda, 1966.
[24] 尚金奎,衷洪杰,赵民,等.TSP转捩探测技术在民机风洞试验中的应用研究[J].空气动力学学报,2016, 34(3):341-345. SHANG J K, ZHONG H J, ZHAO M, et al. Application of TSP transition detection technique for a civil aircraft[J]. Acta Aerodynamica Sinica, 2016, 34(3):341-345(in Chinese).
[25] CATTAFESTA L N, SONG Q, WILLIAMS D R, et al. Active control of flow-induced cavity oscillations[J]. Progress in Aerospace Sciences, 2008, 44:479-502.
[26] LOUIS N C, DAVID R W, CLARENCE W R, et al. Review of active control of flow-induced cavity resonance[C]//33rd AIAA Fluid Dynamics Conference and Exhibit. Reston:AIAA, 2003.
[27] 张超. 超声速方腔流动及控制的数值模拟[D]. 合肥:中国科学技术大学,2016. ZHANG C. Numerical simulation and control of supersonic cavity flows[D]. Hefei:University of Science and Technology of China, 2016(in Chinese).
[28] HELLER H, DELFS J. Cavity pressure oscillations:The generating mechanism visualized[J]. Sound and Vibration, 1966, 196(2):248-252.
CJA