在小展弦比飞翼布局机翼外侧上／下表面分别设计了一组中等后掠角嵌入面，并对其跨声速时的航向控制效果及其流动机理进行了风洞试验和数值模拟研究。计算和试验结果表明，上嵌入面可在小迎角范围通过轴向力和侧向力的共同作用提供稳定的偏航力矩，实现航向控制；当α＞6°时，由于嵌入面逐渐处于前缘涡的影响范围内，在前缘涡的吸力作用下，嵌入面航向控制效果迅速下降，直至失效，且进行航向控制时存在不利的滚转耦合；下嵌入面可在全迎角范围内提供稳定的偏航力矩，实现航向控制；通过在小迎角范围内使用上嵌入面，α＞6°时使用下嵌入面，不仅可在全迎角实现航向控制，且不影响飞机的隐身性能。%The middle sweepback embedded control surfaces are designed on the upper and lower surfaces of a flying-wing,and the control characteristics and flow mechanism are analyzed by both experimental and simulated method.The results show that when the upper embedded control surfaces is opened,there is sufficient yawing moment generated mainly by the side force and drag of embedded control surfaces at small angle of attack.With the increasing of the angle of attack,the embedded control surfaces is under the influence of the leading edge vortex and the directional control ability decreases rapidly,even lapses at high angles of attack.Further more, the embedded control surfaces may have adverse effect on the roll moment because of moment coupling effect.On the other side,the lower embedded control surfaces can functionate as direc-tion control device at all attack angles.Using the lower and upper embedded control surfaces ra-tionaly according to the different angle of attack,it not only the directional control requirement can be guaranteed,but also the stealth performance insured.
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