为了提高所选定飞行器模型的机动性,采用了一种标准遗传算法设计前缘翼根延伸(LEX)。同时使用一种由三维低阶板方法结合DATCOM方法半经验公式的改进方法预测复杂外形飞行器(机身+机翼+尾翼)的空气动力载荷和最大升力系数。结果表明,在前缘翼根存在的情况下,升力系数在马赫数为0.4～0.8时提升了20.5%～15.3%,在马赫数为1.2时提升了6.8%,在马赫数为0.2～0.95之间升力系数最大值提升了9.5%～15%。在1～5km的高度亚音速飞行时,其回转率得到了6.6%～8.0%的提升。 In order to improve the maneuverability of the selected aircraft model, a standard genetic algorithm was used to design the leading edge root extension (LEX). At the same time, an improved method based on semi-empirical formula of DATCOM is used to predict the aerodynamic loads and the maximum lift coefficient of the complex profiled aircraft (fuselage + wing + tail). The results show that the lift coefficient increases by 20.5% ~ 15.3% when Mach number is 0.4 ~ 0.8, 6.8% when Mach number is 1.2, Mach number is 0.2 ~ 0.95 The lift coefficient between the maximum increase of 9.5% to 15%. At 1 ~ 5km altitude subsonic flight, the slew rate has been 6.6% to 8.0% of the upgrade.