某高亚声速鸭式导弹超临界对称翼型设计研究

为改善高亚声速导弹气动性能,提出了超临界对称翼型概念。该翼型具有前缘钝圆,表面平坦,型面面积大等特点。在跨声速、小攻角状态下,翼型表面大部分区域为超声速区,有效防止了激波出现并减轻了边界层分离程度,进而提高了阻力发散马赫数和升阻比。针对某高亚声速鸭式导弹,采用CFD(computational fluid dynamic)软件求解N-S(Navier-Stokes)方程的方法和基于翼型特征的参数描述(PARSEC)方法优化设计了一种超临界对称翼型,并将其应用于鸭舵和尾翼设计。最后,进行了导弹全弹外形的跨声速风洞试验。结果表明:使用超临界对称翼型的高亚声速导弹具有良好的升阻特性。

Study on Supercritical Symmetric Airfoil Design of Certain High Subsonic Canard Missile

A concept of supercritical symmetric airfoil is proposed in order to improve the aerodynamic capability of high subsonic missiles. The airfoil is featured by obtuse rounded leading edge, flat surface and bigger enclosed area. In the case of transonic speed and small angle of attack, supersonic flows exist in most regions of the airfoil surface. The shock wave is efficaciously prevented from occurring and the scope of boundary layer separation is decreased, through which the drag divergence Mach number and the lift-drag ratio are increased. A supercritical symmetric airfoil is designed based on the CFD (computational fluid dynamic) method of solving N-S (Navier-Stokes) equations and the PARSEC (parametric section) method, and is used for the design of canard fin and tail. Transonic wind tunnel test is carried out to verify the aerodynamic capability of the missile with supercritical symmetric airfoil. The results show that the missile with supercritical airfoil has fine lift-drag performance at high subsonic speed.