前体涡诱导机翼摇滚的人工转捩技术研究  

An artificial transition technique applied to wing rock induced by forebody vortex

作　　者：王兵[1] 邓学蓥[1] 马宝峰[1] 荣臻[1] 

机构地区：[1]北京航空航天大学流体力学教育部重点实验室,北京100191

出　　处：《空气动力学学报》2010年第5期525-535,共11页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(10432020;10872019;10702004)

摘　　要：针对翼身组合体由前体绕流主控的机翼摇滚运动现象,在常规低速风洞中为了模拟其前体流动的过临界Re数绕流流态,研究并提出了一种分布式多转捩丝人工转捩技术。该技术是在模型前体的两侧分别以模型周向角±56.25°为中心周向对称分布多对转捩丝,其间隔为22.5°。转捩丝的轴向位置是从x/D=0.306开始延伸到机翼前缘翼根所在截面。在这样的布局下,当模型摇滚时,前体两侧绕流的转捩有效区内就能始终保持至少各有一根转捩丝。这样,在常规低速风洞中进行模型滚转振荡实验时,利用上述人工转捩技术,只要摇滚的减缩频率足够低,在任一滚转角下就能使得前体的边界层流动转捩到过临界流态。最后,在北航D4常规低速风洞中通过该人工转捩技术,得到了在前体过临界Re数绕流流态下,翼身组合体的机翼摇滚运动形态。For the wing rock of wing-body induced by the flow around forebody,an artificial transition technique using distributed multi tripping wires was studied and advanced for simulating the flow around forebody at post-critical Reynolds numbers in a low speed wind tunnel.For this transition technique,several couples of tripping wires were placed longitudinally around the windward surface of the forebody.The tripping wires were all distributed centered at ±56.25° respectively in the azimuth angles by 22.5° on either side of the forebody.And along the x-axis the tripping wires reached the wing tip in the body frame starting from x/D= 0.306,which was from the forebody tip.This layout could ensure that,when the model oscillated in roll,there was at least one tripping wire within the azimuth angles range on either side of the forebody in a wind-axis frame where the tripping wires were effective and efficient for flow transition.Using this method,as long as the reduced frequency was small enough,the flow pattern would always be triggered into post critical pattern at any roll angles of the wing-body model due to oscillation in the experiments in a low speed wind tunnel.At last,this artificial transitional technique was tested in free-to-roll experiments and the time history of wing rock was obtained in the post critical flow regime of the forebody in the D4 low speed wind tunnel of Beijing University of Aeronautics and Astronautics.

关 键 词：机翼摇滚 风洞 人工转捩 过临界 雷诺数 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]