前加载翼型多点综合优化设计

Multi-points Integrated Optimization Design of Fore-loaded Airfoil

前加载翼型具有低头力矩小、隐身性能好的特点,能够对气动和隐身特性进行合理折中,是理想的飞翼布局飞机截面翼型。首先介绍典型翼型参数化方法和评估方法,并对前加载翼型外形的控制能力进行评估,结果表明Hicks-Henne方法和CST方法对前加载翼型外形的控制能力较强,并且CST方法参数个数较少。然后依据飞翼布局飞机设计需求,在确定翼型设计状态和优化设计模型的条件下,将CST翼型参数化方法、N-S方程数值求解方法和遗传算法相结合进行前加载翼型多点综合优化设计,得到比参考翼型具有更大相对厚度和更优气动特性的设计结果。

As fore-loaded airfoil is of less pitching moment and better stealth ability, it can reasonably blend both good aerodynamic and stealth performances at the same time. It is an ideal airfoil for flying wing aircraft. Firstly, typieal parametric methods and evaluation methods are introduced, geometry control abilities of classical airfoil parametric methods are evaluated, and the evaluation results shows that Hicks-Henne and class function/ shape function transformation（CST） method are of more powerful control abilities, and the parameter number is less in CST method. Then, the design states and optimization model are established according to the flying wing aircraft design requirements. The integrated optimization design of fore-loaded airfoil is implemented afterwards with CST parametric method, N-S equation numerical solution method and genetic algorithm, and satisfying design result is obtained. Compared with the reference airfoil, the optimized airfoil has larger relative thickness and better aerodynamic performance.