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大迎角下横向流动引起的外翼过早分离是后掠翼飞机常见的一大问题,对此提出在机翼下翼面安装分离流控制器来抑制流动分离的方案.二维计算中采用Gamma-Theta转捩模型,三维研究使用SST湍流模型,研究发现分离流控制器的设计使流过上翼面的高能气流通量增加,这些高能流体具有更强的抵抗流向逆压梯度的能力,同时阻碍了边界层向外流动,从而改善了外翼的失速性能.通过参数化设计所得的分离流控制器与原始构型相比失速迎角增加,最大升力系数显著提高,阻力系数显著减小,达到了设计目标.
The premature separation of outer wings caused by transverse flow at high angles of attack is a common problem for swept-back aircraft, and a scheme of installing a separate flow controller to suppress flow separation is proposed in this paper. In the two-dimensional calculation, Gamma -Theta transition model, a three-dimensional study using the SST turbulence model. The study found that the design of the split flow controller increases the flux of high-energy gas flowing over the upper airfoil. These energetic fluids have a greater resistance to the flow reversal gradient, Which hinders the outward flow of the boundary layer and thus improves the stalling performance of the outer wing.Compared with the original configuration, the split flow controller obtained by parametric design increases the incidence angle of attack, the maximum lift coefficient increases significantly and the drag coefficient decreases significantly, Achieved the design goal.