This study aims to develop a simple and efficient design optimization methodology for the low Reynolds number airfoils. XFOIL is used as an aerodynamic solver while modeFRONTIER workflow is employed for the design optimization purpose. The airfoil SG6043 is used as the reference airfoil for optimization due to its common applications when long-endurance characteristics are desired. A simple design optimization methodology with the integration of XFOIL in the modeFRONTIER workflow environment is proposed in this study. The proposed “software integration methodology” demonstrated up to 10% improvement in the optimization parameter which makes it more efficient by reducing the optimization time and steps without unnecessary user intervention which are the limitations conventionally associated with the optimization process. The optimization results are further compared with the results of the numerical simulations. The use of the transition-sensitive turbulence model allowed the evaluation of the behavior of the laminar separation bubble for different angles of attack, observing that it shifts towards the leading edge and has its length reduced as the angle of attack increases. The newly generated airfoil exhibits improved aerodynamic characteristics as compared to the base airfoil. The optimized airfoil can be used in the applications of UAVs as well as in general aviation. Further validation of the airfoil using wind tunnel testing is recommended and planned.

本研究旨在为低雷诺数的机翼开发一种简单有效的设计优化方法。XFOIL用作空气动力学求解器，而modeFRONTIER工作流程用于设计优化目的。SG6043机翼由于在需要长期耐力特性时的常见应用而被用作优化的参考机翼。本研究提出了一种在modeFRONTIER工作流环境中集成XFOIL的简单设计优化方法。拟议中的“软件集成方法论”显示出优化参数最多可提高10％，这可以通过减少优化时间和步骤而更加高效，而无需不必要的用户干预，而这通常是与优化过程相关的限制。将优化结果与数值模拟结果进一步进行比较。过渡敏感湍流模型的使用允许评估层流分离气泡在不同迎角下的行为，观察到它朝着前缘移动并且其长度随着迎角的增加而减小。与基础机翼相比，新产生的机翼表现出改进的空气动力学特性。经优化的机翼可用于无人机以及通用航空。建议并计划使用风洞测试进一步验证翼型。过渡敏感湍流模型的使用允许评估层流分离气泡在不同迎角下的行为，观察到它朝着前缘移动并且其长度随着迎角的增加而减小。与基础机翼相比，新产生的机翼表现出改进的空气动力学特性。优化的机翼可用于无人机的应用以及通用航空。建议并计划使用风洞测试进一步验证翼型。过渡敏感湍流模型的使用允许评估层流分离气泡在不同迎角下的行为，观察到它会朝前缘移动并且其长度随着迎角的增加而减小。与基础机翼相比，新产生的机翼表现出改进的空气动力学特性。优化的机翼可用于无人机的应用以及通用航空。建议并计划使用风洞测试进一步验证翼型。优化的机翼可用于无人机的应用以及通用航空。建议并计划使用风洞测试进一步验证翼型。优化的机翼可用于无人机的应用以及通用航空。建议并计划使用风洞测试进一步验证翼型。