中文摘要：

超临界翼型在来流速度超过临界马赫速时会出现激波,导致激波阻力迅速增加,为了减小不同飞行条件下的波阻,本文对激波控制鼓包进行了研究。通过集成NURBS曲线建模和CFD仿真模块搭建了鼓包仿真优化平台,对不同流场状态下的鼓包构型优化。以RAE2822翼型为例进行计算,结果表明在非设计状态下,优化得到的鼓包构型可以大幅度降低翼型激波阻力,提高非设计点的气动效率。为了克服单点优化鼓包减阻有效范围小的问题,提出了一种基于形状记忆合金的二维自适应鼓包设计概念.自适应鼓包能够根据温度调节自身构型,对不同流场状态下的激波进行控制。

英文摘要：

There is a shock wave in the supercritical airfoil when the inflow velocity is faster than tile critical Mach number, which leads to the wave drag increase rapidly. In order to reduce tile wave drag for different flow fields, the shock control bump are studied in this thesis. An optimization platfornl was developed consisting of a genetic algorithm optimiser, a NURBS curve module and a CFD simulation module and the different flow states were optimized by using this platform. A calculation for RAE2822 airfoil has been done, and the computation results demonstrate that tile optimized bump configuration can reduce the wave drag of the airfoil greatly and improve tile performance for off-design conditions. To overcome the problem of narrow effective regions of significant drag reduction for one-point designed bumps, a design of two-dimensional adaptive bump based on shape memory alloy is proposed. Shock wave in different flow condition can be controlled through adjusting the appearance of SMA bump by temperate.