大上翘角机身后体流动机理研究  

Investigation of the flow mechanism on the afterbody with larger upswept angle

作　　者：孔繁美[1] 华俊[1] 冯亚南[1] 邱栋[1] 邓学蓥[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《空气动力学学报》2002年第3期326-331,共6页Acta Aerodynamica Sinica

摘　　要：通过对圆截面上翘 1 6°的后体的数值计算 ,研究了上翘后体的流动机理。结果表明 ,上翘后体引起横向流动 ,使横向逆压梯度增大、下表面边界层增厚 ,导致后体出现三维开式分离流动 ;由分离形成一对方向相反、强度相等的旋涡向下游拖至尾迹区 ;这种分离流动是导致大上翘角后体阻力增加的主要原因。The investigation of the flow mechanism on the afterbody of 16° upswept angle and circle section had been completed by applying a Navier-Stokes method. The results indicated that three-dimensional open separation exists due to the cross flow around the afterbody, thicker boundary layer and the stronger adverse pressure gradient on the lower surface. The vortex pair induced by the separation is developing downstream into the wake of the afterbody. The drag increasing of the larger-upswept afterbody is due to the afterbody separation.

关 键 词：分离流动 旋涡 上翘后体 飞机 机身 数值模拟 流动机理 

分 类 号：V211.42[航空宇航科学与技术—航空宇航推进理论与工程]