This paper proposes an efficient low-speed airfoil selection and design optimization process using multi-fidelity analysis for a long endurance Unmanned Aerial Vehicle (UAV) flying wing. The developed process includes the low speed airfoil database construction, airfoil selection and design optimization steps based on the given design requirements. | TAÏP CHÍ PHAÙT TRIEÅN KH&CN, TAÄP 19, SOÁ K5- 2016 An efficient low-speed airfoil design optimization process using multi-fidelity analysis for UAV flying wing Anh Bao Dinh 1 Khanh Hieu Ngo 1 Nhu Van Nguyen 2 1 Ho Chi Minh City University of Technology, VNU-HCM 2 Konkuk University, South Korea (Manuscript Received on March 22nd, 2016, Manuscript Revised May 30th, 2016) ABSTRACT This paper proposes an efficient low-speed It has low parasite drag, long endurance, and airfoil selection and design optimization process using multi-fidelity analysis for a long endurance better performance. The multi-fidelity analysis solvers are validated for the E387 and Unmanned Aerial Vehicle (UAV) flying wing. The developed process includes the low speed CAL2463m airfoil compared to the wind tunnel test data. Then, 29 low speed airfoils for flying airfoil database construction, airfoil selection wing UAV are constructed by using the multi- and design optimization steps based on the given design requirements. The multi-fidelity analysis fidelity solvers. The weighting score method is used to select the appropriate airfoil for the given solvers including the panel method and computational fluid dynamics (CFD) are design requirements. The selected airfoil is used as a baseline for the inverse airfoil design presented to analyze the low speed airfoil aerodynamic characteristics accurately and optimization step to refine and obtain the optimal airfoil configuration. The implementation of perform inverse airfoil design optimization proposed method is applied for the real flying- effectively without any noticeable turnaround time in the early aircraft design stage. The wing UAV airfoil design case to demonstrate the effectiveness and feasibility of the proposed unconventional flying wing UAV design shows poor reaction in longitudinal stability. However, method. Key words: Low-speed airfoil, airfoil optimization, multi-fidelity analysis, flying wing .
