高超声速飞行器宽速域翼型多目标优化设计研究

高超声速飞行器正向着速域更宽、空域更广、航程更远的方向发展.因而对于现代高超声速飞行器的设计而言,除了保证高超声速的性能外,还必须兼顾满足工程需求的亚声速、跨声速、超声速特性.文章对薄翼型在不同速域下的流动机理进行分析,总结了不同速域下翼型增升减阻的设计准则,然后采用RANS方程流动求解器,结合基于Kriging模型的代理优化算法,开展了高超声速飞行器宽速域翼型的优化设计研究.首先,以NACA64A-204翼型为基准翼型,采用线性加权法进行了考虑亚、跨和高超声速气动特性的多轮次宽速域翼型优化设计研究,得到了一种宽速域性能得到改善的新翼型.然后,以优化得到的新翼型为原始翼型,开展多目标优化设计,获得了宽速域翼型两目标和三目标的Pareto最优化解集.

Multi-Objective Aerodynamic Shape Optimization of Wide-Mach-Number-Range Airfoil

Hypersonic vehicle is developing towards wider speed range, wider airspace range and longer flight range. Therefore, besides the performance at hypersonic cruise, it must also take into account the sub-transonic and supersonic characteristics in the design of wide-Mach-number-range hypersonic aircraft. In this paper, the flow mechanism of thin airfoil in different speed ranges was analyzed, and the design criteria for increasing lift and reducing drag of airfoil in different speed ranges was summarized. Then, the design optimization of wide-Mach-number-range airfoil was carried out by using RANS equation flow solver and surrogate optimization algorithm based on Kriging model. Firstly, using NACA64A-204 airfoil as the baseline, a new airfoil with improved wide-speed performance was obtained by the linear weighting method. Considering the aerodynamic characteristics of sub-transonic and hypersonic flows, the airfoil was designed after multi-round optimization. Then, taking the optimized new airfoil as the original airfoil, multi-objective optimization design was carried out, and the Pareto optimal solution set of two and three objectives for wide-Mach-number range airfoil was obtained.