무인기 공력 성능 향상을 위한 익형 최적 설계

Abstract

A computational study for improving aerodynamic performance was conducted by optimizing the airfoil shape of an Unmanned Aerial Vehicle (UAV). The baseline airfoil, FX73-CL2-152, was selected, and based on this shape, a Kriging approximation model and genetic algorithm were used to find an airfoil shape that maximizes lift and minimizes drag. The optimized airfoil shape was applied to a full-scale model similar to the MQ-1 Predator, and it was confirmed that the lift coefficient and endurance factor increased by 9.5% and 7.3%, respectively. These results demonstrate that the optimization of the airfoil can significantly contribute to the overall performance of the UAV, including reducing takeoff and landing distances, improving structural stability, and increasing fuel load. Furthermore, this research could contribute to enhancing UAVs' operational capabilities and mission performance in various mission environments. In the future, this research can be extended to the optimal design and computational analysis of a full-scale model applied to multi-element airfoils equipped with flaps. It can also be utilized in building a high-accuracy aerodynamic database using high-fidelity DES/LES models.