连接翼布局气动特性研究

The aerodynamics investigation of the joined-wing configuration

在一个小型低速风洞中进行了五种不同布局形式的连接翼方案实验研究。利用油流法研究了三种连接翼的流谱,初步分析了具有连接翼飞机的气流流动机理。为比较,同时对三角翼常规布局方案进行了实验,所有方案使用相类似的隐身布局机身。实验结果表明,连接翼布局有其特有的流型:翼面分前翼、后翼及外翼三部分,其流型受前翼涡、后翼涡、翼端涡、机身边条涡以及它们互相缠绕形成的新涡的控制。这些涡的产生、发展、离体和破裂的情况不同,形成不同方案气动特性的差别。连接翼布局气动特性优于常规翼布局,特别是最大升阻比可达12以上,失速迎角超过30°。通过前后翼后缘操纵面的有利组合,可以达到提高升阻比,满足纵、横向稳定性和操纵性要求的目的。结果显示,具有扁平机身的连接翼方案是一个有潜力的无人机布局形式。

The five joined wing configurations have been experimented in a small wind tunnel. The oil-flow method is employed for undemtanding flow pattern of the joined wings. For the reason of comparison, delta wing layouts have been experimented. The overall confisurations possess similar fiat concealed body. The test results appears that joined-wing layout have special flow-pattern. The wing surface are dominated by the front-wing vorticas, rear-wing vortices, wing-end vorticas and body-side vorticas as well as vorticas that was tied up. These vortices make different aerodynamucs charactem according to distinct vortex state.The joined configuration is superior then common layout, especially, at high angle of attack. Maximum lift-drag ratio is 12. The stalling angle is greeter then 30 degree. The requirements of centmllability and stability of the joined-wing aircraft are satisfied by trailing edge devices. The results show that joined-wlng layout with a fiat cencealed body have great potentialities for the oonfiguration.