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对大型水陆两栖飞机翼型进行了数值优化设计研究,通过以翼型设计升力系数下的阻力系数最小化为设计目标和以翼型低头力矩、最大升力系数、失速后升力系数下降率作为约束条件的大型水陆两栖飞机翼型优化设计,在满足翼型相对厚度、最大厚度位置、最大弯度、最大弯度位置符合相应设计范围的情况下,得到了综合性能较基本翼型提高的新翼型.该设计方法适用于大型水陆两栖飞机的翼型设计,是一种符合工程应用实际的数值优化设计方法.
The numerical optimization design of airfoil for large amphibious aircraft has been carried out. By minimizing the drag coefficient under airfoil design lift and designing the target, taking the airfoil bowing moment, the maximum lift coefficient and the rate of decline of lift coefficient after stall as constraints The airfoil optimization design of large amphibious aircraft has obtained the new aerofoil whose comprehensive performance is higher than that of the basic aerofoil under the condition that the relative thickness, the maximum thickness position, the maximum camber and the maximum camber position meet the corresponding design range. The design method is suitable for the airfoil design of large amphibious aircraft. It is a numerical optimization design method in line with the actual engineering application.