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Boundary-layer and wake measurements on a swept, circulation-control wing

机译:掠过的循环控制机翼的边界层和尾迹测量

摘要

Wind-tunnel measurements of boundary-layer and wake velocity profiles and surface static pressure distributions are presented for a swept, circulation-control wing. The model is an aspect-ratio-four semispan wing mounted on the tunnel side wall at a sweep angle of 45 deg. A full-span, tangential, rearward blowing, circulation-control slot is located ahead of the trailing edge on the upper surface. Flow surveys were obtained at mid-semispan at freestream Mach numbers of 0.425 and 0.70. Boundary-layer profiles measured on the forward portions of the wing are approximately streamwise and two dimensional. The flow in the vicinity of the jet exit and in the near wake is highly three dimensional. The jet flow near the slot on the Coanda surface is directed normal to the slot. Near-wake surveys show large outboard flows at the center of the wake. At Mach 0.425 and a 5-deg angle of attack, a range of jet-blowing rates was found for which an abrupt transition from incipient separation to attached flow occurs in the boundary layer upstream of the slot. The variation in the lower-surface separation location with blowing rate was determined from boundary-layer measurements at Mach 0.425.
机译:提出了掠过的,循环控制的机翼的边界层和尾流速度剖面的风洞测量以及表面静压力分布。该模型是纵横比为四个的半跨翼,以45度的后掠角安装在隧道侧壁上。一个全跨度,切向,向后吹的循环控制槽位于上表面的后缘之前。流量调查是在半跨中期进行的,自由流马赫数分别为0.425和0.70。在机翼前部测得的边界层轮廓大致呈水流方向和二维。射流出口附近和近尾流处的流动是高度三维的。柯恩达表面上狭缝附近的射流垂直于狭缝定向。近尾流调查显示,尾流中心处有大量舷外流量。在0.425马赫和5度迎角的情况下,发现了一定范围的喷射速率,在该速率范围内,在缝隙上游的边界层中发生了从初始分离到附着流动的突然转变。下表面分离位置随吹气速度的变化是根据边界层测量值在0.425马赫时确定的。

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