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针对翼面部件对隐身飞机气动和隐身性能影响更为突出的问题,提出了一种翼型前缘参数化修形方法,采用高精度气动和电磁数值计算方法,进行了前缘形状对翼型气动-隐身特性的敏感性分析。研究结果表明:翼型前缘半径增加,其最大升力系数、失速迎角、最大升阻比显著增加,但其前向RCS均值也增加明显,设计时需进行综合权衡;在不影响结构和装载的情况下,下表面偏角尽量小,修形长度取0.15c,对翼型的低、高速气动和隐身特性都有利。
Aiming at the problem that airfoil parts have a more prominent impact on the aerodynamic and stealth performance of stealth aircraft, a parametric method of airfoil leading edge modification is proposed. By using high precision aerodynamic and electromagnetic numerical methods, Sensitivity Analysis of Aerodynamic - Stealth Characteristics. The results show that the radius of the leading edge of the airfoil increases, the maximum lift coefficient, the angle of attack at attack, the maximum lift-drag ratio increase significantly, but the forward RCS mean value also increases obviously. The design needs to be comprehensively weighed. Without affecting the structure and loading Of the case, the lower surface of the declination as small as possible to shape the length of 0.15c, the airfoil low, high-speed aerodynamic and stealth features are beneficial.