攻角拉起时前体非对称涡诱导机翼摇滚运动

徐思文; 邓学蓥; 王延奎

doi:10.13700/j.bh.1001-5965.2014.0707

攻角拉起时前体非对称涡诱导机翼摇滚运动

doi: 10.13700/j.bh.1001-5965.2014.0707

北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 国家自然科学基金(11172030);国家自然科学青年科学基金(11102012)

详细信息

作者简介:
徐思文(1987-),男,安徽六安人,博士研究生,mist1987@163.com

通讯作者:
邓学蓥(1941-),男,北京人,教授,dengxueying@vip.sina.com,研究方向为大攻角空气动力学.

中图分类号: V211.7
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出版历程
- 收稿日期: 2014-11-17
- 修回日期: 2015-02-05
- 网络出版日期: 2015-11-20

Wing rock motion induced by forebody asymmetric vortices in pitch-up

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对目前前体非对称涡诱导机翼摇滚研究时攻角往往处于静态而没有考虑攻角动态拉起的问题,在北航D4风洞中采用细长旋成体与30°后掠翼的组合体模型,通过不同拉起速度下的机翼摇滚运动实验,分析了攻角拉起速度对前体非对称涡诱导机翼摇滚运动的影响及影响产生的原因;随后通过在快速拉起摇滚运动过程中进行模型表面压力测量,研究了快速拉起机翼摇滚的流动机理.实验结果表明,由于机翼摇滚运动的时间随攻角拉起速度增加而减少,使得在3个不同的拉起速度分区内,摇滚运动呈现为不同的运动形态,其中第3个快速拉起分区内的摇滚运动为与攻角静态时完全不同的类正弦摇滚运动形态.与攻角静态时机翼摇滚的流动机理不同,快速拉起时这种类正弦摇滚运动主要源于前体非对称涡随攻角的演化,前体非对称涡随滚转角的涡型切换不再重要.
- 攻角拉起 /
- 前体非对称涡 /
- 机翼摇滚 /
- 类正弦运动 /
- 流动机理
Abstract: Aiming to the issue that the angle of attack was usually fixed rather than pitched-up in the previous researches about the wing rock induced by forebody asymmetric vortices, series of wind tunnel experiments were conducted in Beihang University D4 wind tunnel over the configuration of a pointed ogive-cylindrical body with 30° swept wings. Effect of pitch rate on wing rock motion as well as the mechanism of that was first studied through wing rock experiments in different pitch rates. The flow mechanism of wing rock in high rate pitch-up was then studied through the surface pressure measurements during the dynamic wing rock. Experimental results show that, as the wing rock motion time reduces with increase of pitch rate, the motion patterns of wing rock are different in three different intervals of pitch rate. The sinusoidal-like motion, which is totally different from the motion at static angle of attack, would occur in the third interval with high rate pitch-up. The variation of forebody flow with angle of attack, instead of the variation of forebody flow with roll angle, is found to be responsible for the sinusoidal-like motion in high rate pitch-up. Hence, the flow mechanism of wing rock in pitch-up is greatly different from that at static angle of attack.
- pitch-up /
- forebody asymmetric vortices /
- wing rock /
- sinusoidal-like motion /
- flow mechanism

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参考文献(26)

[1]	Katz J.Wing/vortex interactions and wing rock[J].Progress in Aerospace Sciences, 1999, 35:727-750.
[2]	Quast T, Nelson R C, Fisher D F.A study of high alpha dynamics and flow visualization for a 2.5% model of the F-18 HARV undergoing wing rock[J].AIAA, 1991, 3267-CP:524-533.
[3]	Klein V, Noderer K D.Aerodynamic parameters of the X-31 drop model estimated from flight data at high angles of attack[J].AIAA, 1992, 4357:174-181.
[4]	Brandon J M, Nguyen L T.Experimental study of effects of forebody geometry on high angle of attack stability[J].Journal of Aircraft, 1988, 25(7):591-597.
[5]	Ericsson L E.Wing rock generated by forebody vortices[J].Journal of Aircraft, 1989, 26(2):110-116.
[6]	Ericsson L E.Further analysis of wing rock generated by forebody vortices[J].Journal of Aircraft, 1989, 26(12):1098-1104.
[7]	马宝峰.前体涡诱导机翼摇滚的实验研究[D].北京:北京航空航天大学, 2007. Ma B F.Experimental investigation of roll oscillation induced by forebody vortex[D].Beijing:Beihang University, 2007(in Chinese).
[8]	Wang B, Deng X Y, Ma B F, et al.Effect of tip perturbation and wing locations on rolling oscillation induced by forebody vortices[J].Acta Mechanica Sinica, 2010, 26(5):787-791.
[9]	荣臻.前体涡诱导机翼摇滚的流动特性及机理研究[D].北京:北京航空航天大学, 2009. Rong Z.An experimental investigation on flow characteristics and mechanism of wing rock induced by forebody vortex[D].Beijing:Beihang University, 2009(in Chinese).
[10]	Dexter P C, Hunt B L.The effect of roll angle on the flow over a slender body of revolution at high angles of attack[J].AIAA, 1981, 0358:1-13.
[11]	Zilliac G G, Degani D, Tobak M.Asymmetric vortices on a slender body of revolution[J].AIAA, 1991, 29(5):667-675.
[12]	Dexter P C.A study of asymmetric flow over slender bodies at high angles of attack in a low turbulence environment[J].AIAA, 1984, 0505:1-11.
[13]	Moskovitz C A, Raleigh N C, Hall R M, et al.Effects of surface perturbations on the asymmetric vortex flow over a slender body[J].AIAA, 1988, 0483:1-10.
[14]	Moskovitz C A, Hall R M, Dejarnette F R.Effects of nose bluntness, roughness and surface perturbations on the asymmetric flow past slender bodies at iarge angles of attack[J].AIAA, 1989, 2236-CP:720-732.
[15]	Chen X R, Deng X Y, Wang Y K, et al.Influence of nose perturbations on behaviors of asymmetric vortices over slender body[J].Acta Mechanica Sinica, 2002, 18(6):581-593.
[16]	Hunt B L.Asymmetric vortex forces and wakes on slender bodies[J].AIAA, 1982, 1336:1-41.
[17]	Lamont P J.Pressures around an inclined ogive cylinder with laminar, transitional, or turbulent separation[J].AIAA, 1982, 20(11):1492-1499.
[18]	Li Y P, Ge F Y, Lan C E.Estimation of aircraft models in cobra maneuver through dynamic inversion[J].AIAA, 1994, 3494-CP:322-332.
[19]	Alcorn C W, Croom M A, Francis M S, et al.The X-31 aircraft:Advances in aircraft agility and performance[J].Progress in Aerospace Sciences, 1996, 32:377-413.
[20]	田伟.细长旋成体及融合体型机身大迎角背涡流动特性研究[D].北京:北京航空航天大学, 2010. Tian W.Study on behaviors of leeward vortices over slender body and chined fuselage at high angle of attack[D].Beijing:Beihang University, 2010(in Chinese).
[21]	曹博超.风洞动态测压技术及其在机翼摇滚运动研究中的应用[D].北京:北京航空航天大学, 2008. Cao B C.Dynamic pressure measurement technology in the wind tunnel and its application in the investigation of wing-rock phenomenon[D].Beijing:Beihang University, 2008(in Chinese).
[22]	王刚,邓学蓥,王延奎,等.亚临界雷诺数细长体绕流流态随迎角的变化和分区[J].流体力学实验与测量, 2003, 17(2):19-26. Wang G, Deng X Y, Wang Y K, et al.Zonal study of flow patterns around an ogive-cylinder at subcritical reynolds numbers[J].Experiments and Measurements in Fluid Mechanics, 2003, 17(2):19-26(in Chinese).
[23]	Lamont P J, Hunt B L.Pressure and force distributions on a sharp-nosed circular cylinder at large angles of inclination to a uniform subsonic stream[J].J Fluid Mech, 1976, 76(3):519-559.
[24]	Keener E R, Chapman L C, Talegbani J.Side forces on a tangent ogive forebody with a fineness ratio of 3.5 at high angles of attack and mach numbers from 0.1 to 0.7[J].NASA, 1977, TM, X-3437:1-109.
[25]	Ericsson L E, Reding J P.Aerodynamic effects of asymmetric vortex shedding from slender bodies[J].AIAA, 1985, 1797:222-256.
[26]	Lamont P J.Pressures around an inclined ogive cylinder with laminar, transitional, or turbulent[J].AIAA, 1980, 1556R:1-10.