尖侧缘机身布局的俯仰力矩特性及扰流板控制

doi:10.7527/S1000-6893.2018.22448

流体力学与飞行力学

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尖侧缘机身布局的俯仰力矩特性及扰流板控制

李乾¹, 董超², 齐中阳¹, 王延奎¹

1. 北京航空航天大学航空科学与工程学院, 北京 100083;
2. 北京航天长征飞行器研究所, 北京 100076

收稿日期:2018-06-13 修回日期:2018-07-22 出版日期:2019-04-15 发布日期:2018-08-27
通讯作者: 王延奎 E-mail:wangyankui@buaa.edu.cn
基金资助:
国家自然科学基金（11472028，11721202）；航空科学基金（2016ZA51007）

Pitching moment character and its control using forebody spoiler over a configuration with chined fuselage

LI Qian¹, DONG Chao², QI Zhongyang¹, WANG Yankui¹

1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China;
2. Beijing Long March Aerospace Vehicle Research Institute, Beijing 100076, China

Received:2018-06-13 Revised:2018-07-22 Online:2019-04-15 Published:2018-08-27
Supported by:
National Natural Science Foundation of China (11472028, 11721202); Aeronautical Science Foundation of China (2016ZA51007)

摘要/Abstract

摘要： 针对尖侧缘机身布局在大迎角下存在的正俯仰力矩（抬头力矩）问题，通过风洞试验，首先研究了俯仰力矩的迎角分区特性及流动演化规律：线性增长区（迎角为0°~15°），俯仰力矩线性增加，全机从附着流到形成进气道前缘涡和机翼涡；非线性增长区（迎角为17.5°~32.5°），俯仰力矩非线性增加，机头涡出现，机头涡和进气道前缘涡逐渐增强，机翼涡增强后破裂；衰减区（迎角为35°~65°），俯仰力矩逐渐减小，机头涡增强后破裂，进气道前缘涡破裂发展，机翼涡完全破裂。其次，发现了机身前体是产生正俯仰力矩的主要来源，机头涡是导致大迎角下正俯仰力矩的主控流动。当迎角为40°时，前体各截面正俯仰力矩在进气道前缘处达到最大，主要是由于该处机头涡诱导产生了较强的法向力。最后，提出了大迎角机身扰流板控制技术，产生了较好的控制效果。当迎角为40°时，扰流板可使正俯仰力矩减少62%，其原因是扰流板降低了机头涡涡量及其诱导产生的法向力，减少了机身前体对正俯仰力矩的贡献。该控制技术的缺点是扰流板会带来一些升力损失和附加阻力。基于尖侧缘机身参考宽度的雷诺数为2.59×10⁵。

关键词: 尖侧缘机身, 正俯仰力矩, 机身扰流板, 大迎角, 风洞试验

Abstract: Wind tunnel experiments are conducted to understand the positive pitching moment of a configuration with chined forebody at high angles of attack. Firstly, the trend of pitching moments with angles of attack can be divided into zones of linear growth (0°-15° angle of attack), nonlinear growth (17.5°-32.5° angle of attack) and decay (35°-65° angle of attack). In the zone of linear growth, the pitching moment increases linearly, and the attached flowis observedat first and the inlet leading-edge vortex and wing vortex begin to form as the angles of attack increase. In the nonlinear growth zone, the pitching moment increases nonlinearly, and the nose vortex appears and becomes incrementally strong. Both the inlet leading-edge vortex and wing vortex become more intensive and then begin to burst. In the decay zone, the pitching moment gradually decreases and the nose vortex continues to strengthen and break down at a sufficient high angle of attack. The inlet leading-edge vortex exhibits a decay trend while the wing vortex completely bursts. Secondly, it is observed that the chined forebody is the main contribution component to the positive pitching moment. And the nose vortex over the chine forebody plays a dominant role in generating the positive pitching moment. At 40° angle of attack, due to the strong suction of the nose vortex, the sectional pitching moments reach the maximum at the leading edge of the inlet. In the end, the technique using a forebody spoiler is developed to control the positive pitching moments effectively at high angles of attack. With the forebody spoiler on, the positive pitching moment can be reduced by 62% at 40° angle of attack because by deploying the forebody spoiler, the vorticity of nose vortex is decreased and results in a reduced normal force and positive pitching moment provided by the chined forebody. The downside of the control technique is that the forebody spoiler may lead to some losses in lift and additional drag. The Reynolds number in this paper is 2.59×10⁵ based on the characteristic width of the chined fuselage.

Key words: chined forebody, positive pitching moment, forebody spoiler, high angle of attack, wind tunnel experiments

中图分类号:

V211.7

李乾, 董超, 齐中阳, 王延奎. 尖侧缘机身布局的俯仰力矩特性及扰流板控制[J]. 航空学报, 2019, 40(4): 122448-122448.

LI Qian, DONG Chao, QI Zhongyang, WANG Yankui. Pitching moment character and its control using forebody spoiler over a configuration with chined fuselage[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(4): 122448-122448.

参考文献

[1] ROOS F W, KEGELMAN J T. Aerodynamic characteristics of three generic forebodies at high angles of attack[C]//29th Aerospace Sciences Meeting. Reston, VA:AIAA, 1991:21437.
[2] KEGELMAN J T, ROOS F W. Influence of forebody cross-section shape on vortex flowfield structure at high alpha[C]//9th Applied Aerodynamics Conference. Reston, VA:AIAA, 1991:53867.
[3] MANGE R L, ROOS F W. The aerodynamics of a chined forebody[C]//29th Fluid Dynamics Conference. Reston, VA:AIAA, 1998:2903.
[4] HALL R M. Influence of forebody cross-sectional shape on wing vortex burst location[C]//4th Applied Aerodynamics Conference. Reston, VA:AIAA, 1986:37845.
[5] LOWSON M V, PONTON A J. Symmetry breaking in vortex flows on conical bodies[J]. AIAA Journal, 1992, 30(6):1576-1583.
[6] TIAN W, DENG X Y, WANG Y K, et al. Study on flow behavior and structure over chined fuselage at high angle of attack[J]. Science China Technological Sciences, 2010, 53(8):2057-2067.
[7] SHI W, DENG X Y, TIAN W, et al. Influence of artificial tip perturbation on asymmetric vortices flow over a chined fuselage[J]. Chinese Journal of Aeronautics, 2015, 28(4):1016-1022.
[8] MA B F, DENG X Y. Vortex Interactions between chined forebody and strake[J]. Journal of Aircraft, 2006, 43(6):1953-1955.
[9] MA B F, DENG X Y. Tip-disturbance effects on asymmetric vortex breakdown around a chined forebody[J]. Journal of Aircraft, 2008, 45(4):1098-1104.
[10] 杨其德, 马明生, 余涛, 等. 一个非常规前体机身的流动显示研究[J]. 流体力学实验与测量, 1999, 13(1):64-72. YANG Q D, MA M S, YU T, et al. Flow visualization for an unconventional forebody[J]. Experiments and Measurements in Fluid Mechanics, 1999, 13(1):64-72(in Chinese).
[11] ROOS F W, MAGNESS C L. Yaw Effects on the high-alpha flow field of a chined forebody[C]//32nd Aerospace Sciences Meeting and Exhibit. Reston, VA:AIAA, 1994:0073.
[12] 刘刚, 邱玉鑫. 具有尖侧缘的非圆截面机身头部几何参数影响研究[J]. 实验流体力学, 2006, 20(4):54-58. LIU G, QIU Y X. Investigation of unconventional fore-body section geometry parameter's effect[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(4):54-58(in Chinese).
[13] SHI W, DENG X Y, WANG Y K. Interaction of asymmetric vortices over chined forebody/wing configuration at high angles of attack[C]//Asian-Pacific Conference on Aerospace Technology and Science, 2013:317-327.
[14] ERICKSON G E, BRANDON J M. On the nonlinear aerodynamic and stability characteristics of a generic chine-forebody slender-wing fighter configuration[C]//5th Applied Aerodynamics Conference. Reston, VA:AIAA, 1987:49114.
[15] ERICKSON G E, BRANDON J M. Low-speed experimental study of the vortex flow effects of a fighter forebody having unconventional cross-section[C]//12th Atmospheric Flight Mechanics Conference. Reston, VA:AIAA, 1985:43851.
[16] HALL R M. Impact of fuselage cross section on the stability of a generic fighter[C]//16th Applied Aerodynamics Conference. Reston, VA:AIAA, 1998:32477
[17] JEANS T L, MCDANIEL D R, CUMMINGS R M, et al. Aerodynamic analysis of a generic fighter using delayed detached-eddy simulation[J]. Journal of Aircraft, 2009, 46(4):1326-1339.
[18] MULLIN S. The evolution of the F-22 advanced tactical fighter(1992 Wright Brothers Lecture)[C]//Flight Simulation Technologies Conference. Reston, VA:AIAA, 1992:4188.
[19] NGUYEN L T, FOSTER J V. Development of a preliminary high-angle-of-attack nose-down pitch control requirement for high-performance aircraft:NASA-TM-101684[R]. Washington, D.C.:NASA, 1990.
[20] OGBURN M E, FOSTER J V, WILSON J, et al. Status of the validation of high-angle-of-attack nose-down pitch control margin design guidelines[C]//Flight Simulation and Technologies. Reston, VA:AIAA, 1993:3623.
[21] LACKEY J. Pitch control margin at high angle of attack-quantitative requirements[C]//28th National Heat Transfer Conference. Reston, VA:AIAA 1992:4107.
[22] BERRIER B L, RE R J. A review of thrust-vectoring schemes for fighter aircraft[C]//14th Joint Propulsion Conference. Reston, VA:AIAA, 1978:1023.
[23] 钱丰学, 梁贞桧. 现代战斗机纵横向稳定性改进研究[C]//全国低跨超声速空气动力学文集第一卷. 北京:中国空气动力学会, 2001:116-120. QIAN F X, LIANG Z H. Improvement of longitudinal and lateral stability of modern aircraft[C]//Proceedings of National Conference on Subsonic, Transonic and Supersonic Aerodynamics. Beijing:CARS, 2001:116-120(in Chinese).
[24] DONG C, DENG X Y, WANG Y K, et al. A new criterion to determine the position of vortex breakdown point[C]//Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology. Xi'an:CSAA, 2010:137-140.

E-mail：hkxb@buaa.edu.cn

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尖侧缘机身布局的俯仰力矩特性及扰流板控制

Pitching moment character and its control using forebody spoiler over a configuration with chined fuselage

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