超声速弹翼剖面形状气动性能影响分析

Analysis of Aerodynamic Performance’s influence of Supersonic Missile Wings with Different Profile Shapes

为研究超声速状态下不同剖面形状弹翼的气动性能影响,本文设计了具有相同面积和展弦比的弧形剖面、菱形剖面及六边形剖面三种弹翼,采用CFD数值模拟方法分别计算在0°、5°、10°及15°迎角下,马赫数从0.8到2变化时,分别比较三种不同剖面形状弹翼的升力系数、阻力系数及升阻比,分析了三种不同剖面形状弹翼的气动特性。结果表明,在不同的迎角下,三种不同剖面形状弹翼中,菱形剖面弹翼的升阻比特性最好,其激波阻力最小,六边形剖面弹翼的阻力特性最差,三种弹翼的升力特性差距不大。

In order to research the aerodynamic performance of the missile wings with different profile shapes under supersonic condition,three different kinds of missile wing profiles with the same area and aspect ratio,i.e.,arc profile,diamond profile and hexagonal profile,are designed in this thesis.The lift coefficient,drag coefficient and lift-drag ratio of missile’s wing with three different profile shapes are calculated by CFD numerical simulation at angles of attack of 0°,5°,10°and 15°,when Mach number varies from 0.8 to 2.Aerodynamic characteristics of three kinds of missile wings with different profile shapes were comparably analyzed.The results show that,at different angles of attack,among the three kinds of missile wings with different profiles,the diamond profile wing has the best lift-to-drag ratio characteristic and the smallest wave drag,and the hexagonal profile wing has the worst drag characteristic.There is not much difference in the lift characteristics of the three kinds of wings.