新概念机翼尾流特性实验

doi:10.7527/S1000-6893.2016.0239

流体力学与飞行力学

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新概念机翼尾流特性实验

朱睿¹, 刘锦生², 刘志荣¹, 鲍锋¹

1. 厦门大学航空航天学院, 厦门 361005;
2. 清华大学航天航空学院, 北京 100084

收稿日期:2016-03-23 修回日期:2016-08-21 出版日期:2017-04-15 发布日期:2016-08-23
通讯作者: 鲍锋 E-mail:fbao@xmu.edu.cn
基金资助:
国家自然科学基金（11072206）；福建省科学基金（2012J01023）

Experiment on a new concept wing layout with alleviated wake vortex

ZHU Rui¹, LIU Jinsheng², LIU Zhirong¹, BAO Feng¹

1. School of Aeronautics and Astronautics, Xiamen University, Xiamen 361005, China;
2. School of Aerospace, Tsinghua University, Beijing 100084, China

Received:2016-03-23 Revised:2016-08-21 Online:2017-04-15 Published:2016-08-23
Supported by:
National Natural Science Foundation of China (11072206); Science Foundation of Fujian Province of China (2012J01023)

摘要/Abstract

摘要：

大型飞机常采用开启襟翼以增大机翼升力系数，实现较大迎角的起飞和降落，而机翼在大迎角状态下，翼尖会产生能量集中且自由消散时间长的飞机尾涡，严重影响后续起降飞机的安全。基于Rayleigh-Ludwieg不稳定性，提出一种新概念飞机襟翼布局，通过水槽实验发现：新概念布局的襟翼对翼尖涡的消散具有明显的促进作用，不同参数组合下襟翼涡对翼尖涡的运动特性和能量变化的影响均有不同。实验结果也为飞机尾流控制的研究提供了参考，在满足飞行力学设计的基础上，合理运用增升装置构建四涡系统可以有效促进飞机尾流的消散，提高机场飞机起降效率。

关键词: 飞机尾涡, Rayleigh-Ludwieg不稳定性, 襟翼, 粒子图像测速, 水槽

Abstract:

Aircraft wake vortex will be produced by the wing tip to have a negative impact on flight safety, when a large aircraft applies flap wing to take-off and landing under a large angle of attack. Based on the Rayleigh-Ludwieg instability, a new concept flap layout is developed by adding a set of specially designed flaps. Water channel experiments reveal that the new concept flap layout can significantly promote the wingtip vortex dissipation. The wingtip vortex which is affected by flap vortex with disparate parameter combinations performs differently with respect to movement characteristics and energy. The experiments also provide references to wake vortex control, when the requirement for flight mechanics design is satisfied. Building four-vortex system reasonably by taking advantage of high-lift devices will has a significant effect on alleviating the intensity of aircraft wake, and improve the efficiency of aircraft take-off and landing at the airport.

Key words: aircraft wake vortex, Rayleigh-Ludwieg instability, flap, particle image velocimetry, water channel

中图分类号:

V211.76

朱睿, 刘锦生, 刘志荣, 鲍锋. 新概念机翼尾流特性实验[J]. 航空学报, 2017, 38(4): 120250-120250.

ZHU Rui, LIU Jinsheng, LIU Zhirong, BAO Feng. Experiment on a new concept wing layout with alleviated wake vortex[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(4): 120250-120250.

参考文献

[1] 鲍锋, 刘锦生, 朱睿, 等. 飞机尾涡系Rayleigh-Ludwieg不稳定性实验研究[J]. 航空学报, 2015, 36(7):2166-2176. BAO F, LIU J S, ZHU R, et al. Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortexs[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(7):2166-2176 (in Chinese).
[2] BREISAMTER C. Wake vortex characteristics of transport aircraft[J]. Progress in Aerospace Sciences, 2010, 47(2):89-134.
[3] GERZ T, HOLZAPFEL F, BRYANT W, et al. Research towards a wake-vortex advisory system for optimal aircraft spacing[J]. Comptes Rendus Physique, 2005, 6(4-5):501-523.
[4] SPALART P R. Airplane trailing vortices[J]. Annual Review of Fluid Mechanics, 1998, 30(1):107-138.
[5] BAO F, VOLLMERS H, MATTNER H. Experimental study on controlling wake vortex in water towing tank[C]//20th International Congress on Instrumentation in Aerospace Simulation Facilities. Piscataway, NJ:IEEE Press, 2003:214-223.
[6] LIU Y, WANG J W, LIU Z R, et al. Experimental investigation of wake vortex in a water towing tank[C]//6th International Symposium on Advanced Optical Manufacturing and Testing Technologies:Optical Test and Measurement Technology and Equipment, 2012:314-322.
[7] LIU Y, ZHANG Z F, YANG Q, et al. Experimental investigation of counter-rotating two vortices in water towing tank[C]//2010 IEEE International Conference on Intelligent Computing and Intelligent Systems. Piscataway, NJ:IEEE Press, 2010:274-278.
[8] 刘志荣, 朱睿. 双翼尖涡Rayleigh-Ludwieg不稳定性实验研究[J]. 实验流体力学, 2013, 27(2):24-30. LIU Z R, ZHU R. Dual wingtips vortexes Rayleigh-Ludwieg instability experimental research[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(2):24-30 (in Chinese).
[9] RENNICH S C, LELE S K. Method for accelerating the destruction of aircraft wake vortices[J]. Journal of Aircraft, 1999, 36(2):398-404.
[10] RENNICH S C, LELE S K. Method for accelerating the destruction of aircraft wake vortices[J]. Journal of Aircraft, 1999, 36(2):398-404.
[11] EIKE S. Numerical study of four-vortex aircraft wakes and layout of corresponding high-lift congurations[C]//42nd Aerospace Sciences Meeting and Exhubit. Reston:AIAA, 2004.
[12] BRISTOL R L, ORTEGA J M, MARCUS P S, et al. On cooperative instabilities of parallel vortex pairs[J]. Journal of Fluid Mechanics, 2004, 517:331-358.
[13] SAVAS Ö. Experimental investigations on wake vortices and their alleviation[J]. Comptes Rendus Physique, 2005, 6(4-5):415-429.
[14] CROUCH J. Airplane trailing vortices and their control[J]. Comptes Rendus Physique, 2005, 6(4-5):478-499.
[15] JACQUIN L, FABRE D, SIPP D, et al. Unsteadiness, instability and turbulence in trailing vortices[J]. Comptes Rendus Physique, 2005, 6(4-5):399-414.
[16] KAUERTZ S, NEUWERTH G. Excitation of instabilities in the wake of an airfoil by means of active winglets[J]. Aerospace Science and Technology, 2006, 10(7):551-562.
[17] HE Y, YANG J W, BAO F. Wake vortex control using modified flaps[J]. Applied Mechanics and Materials, 2013, 365:827-834.
[18] 鲍锋, 朱睿, 刘志荣, 等. 四涡尾流系统的构建及其特性的实验研究[J]. 航空学报, 2015, 36(5):1491-1499. BAO F, ZHU R, LIU Z R, et al. Four-vortex wake system reconstruction and their experimental study on its wake features[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(5):1491-1499 (in Chinese).
[19] 鲍锋, 刘锦生, 朱睿, 等. 基于涡系相交不稳定性的飞机尾流控制方法[J]. 北京航空航天大学学报, 2015, 41(8):1381-1387. BAO F, LIU J S, ZHU R, et al. Control method for aircraft wake vortex base on Rayleigh-Ludwig instability[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(8):1381-1387 (in Chinese).
[20] BREITSAMTER C. Wake vortex characteristics of transport aircraft[J]. Progress in Aerospace Sciences, 2011, 47(2):89-134.
[21] BORER N K, BARROWS T M, LEVINE D M, et al. Formation airdrop scaling effects on aircraft wake vortex formation and interaction[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 2013.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

新概念机翼尾流特性实验

Experiment on a new concept wing layout with alleviated wake vortex

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