基于涡流发生器的风洞侧壁附面层控制  

Wind tunnel side wall boundary layer control based on vortex generator

作　　者：刘光远[1] 王瑞波[1] 邓吉龙[1] 陈宏涛[1] 

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000

出　　处：《航空动力学报》2016年第9期2140-2145,共6页Journal of Aerospace Power

摘　　要：为降低风洞侧壁附面层对半模型数据的影响,在前期数值模拟的基础上,研制了一种适用于2.4m跨声速风洞半模型试验段侧壁的梯形涡流发生器,并进行了试验验证.结果表明：加装涡流发生器效果明显,亚声速范围内能够使附面层厚度降低20%-30%,对主气流均匀性影响可忽略;加装后半模型零升阻力系数降低,升力线斜率增大,压力中心向机身移动,体现了明显的附面层减薄效果,证明所研制的涡流发生器可应用于亚声速半模型试验中.Combined with former numerical simulating results, vortex generators applicable for 2.4 m transonic wind tunnel half-model test section were designed and validated to reduce side wall boundary layer effect. Results show that 20%-30% boundary layer thickness is reduced using trapezia-shaped flat vortex generators in subsonic conditions, and the influence on flow field uniformity is neglectable. The decrease of zero-lift drag and increase of lift-slope are found after vortex generators installation, meanwhile pressure center moves toward fuselage. Both trends are distinct evidence of thinner boundary layers. The developed vortex generators can be applied to half-model tests for subsonic conditions.

关 键 词：风洞 涡流发生器 附面层厚度 半模型试验 流动控制 

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]