【作者】 陆超；

【导师】 申振华；

【作者基本信息】 沈阳航空工业学院 ， 航空宇航推进理论与工程， 2009， 硕士

【摘要】 超临界翼型由于拥有良好的跨声速气动性能,而被广泛应用于民航飞机、运输机和轰炸机等高亚声速巡航飞机上。而二维翼型的设计,是三维机翼的基础,因此,设计人员在对二维超临界翼型的研究上,花费了大量精力。鉴于此,本文选取某超临界翼型,探讨改型对超临界翼型气动性能的影响。本文采用翼型正设计方法以及计算流体力学基本原理,对NPU-S 73613翼型进行数值模拟,首先根据已公布的翼型实验数据,对原翼型进行计算,来验证软件和算法的可靠性。而后通过修改不同的翼型参数,这其中包括厚度、弯度、前缘半径、以及尾缘厚度,研究翼型气动性能的变化。最后根据前述计算结果和已有的经验,在原翼型的基础上,推出两种新的改型方案,达到改善原翼型气动性能的目的。计算结果表明,厚度、厚度位置和发散尾缘的变化,对翼型的气动性能影响很大,特别是最大厚度位置和发散尾缘的调整,在减弱激波强度,推迟临界马赫数方面效果明显。改型1在新的设计状态下升阻比下降了2.14%;而改型2的升阻比则提高了2.67%,使原翼型在跨声速阶段气动性能有了一定的提高。更多还原

【Abstract】 The supercritical airfoil has been widely used in high subsonic cruise aircraft, such as civil aircraft, transport aircraft and bomber aircraft, due to their good transonic aerodynamic performance. For two dimensional airfoil design, the researchers put massive effort since it is the basis of the three dimensional wing design. This thesis investigated the effect of the airfoil modification on the areodynamic performance of a certain supercritical airfoil.Using airfoil direct problem design method, based on published airfoil test data, this work calculated the original airfoil NPU-S 73613 and verified the reliability of the software and algrithom by applying Fluent commercial software. Furthermore, this research investigated the change of the airfoil aerodynamic performance by modifying different airfoil parameters, such as thickness, camber, leading edge radius and trailing edge thickness. Lastly, this thesis proposed two new modified airfoils on the basis of the original airfoil according to previous results and experiences in order to improve the aerodynamic performance of the original airfoil.The predicted results showed that the effect of the modification of thickness, its location and divergent trailing edge on the aerodynamic feature is dramatic. Especially the modification of the location of the maximum thickness and divergent trailing edge has significant influence on the reduction of the intensity of the shock wave and the delay of the critical March number. In comparison to the original airfoil, the lift to drag ratio for the modification 1 and 2 increased -2.14% and 2.67% respectively, which indicated the remarkable improvement of the transonic aerodynamic performance to the original airfoil.更多还原