Numerical and experimental investigation to design a novel morphing airfoil for performance optimization
Numerical and experimental investigation to design a novel morphing airfoil for performance作者机构：Faculty of AerospaceMalek Ashtar University of TechnologyTehran 1774-15875Iran School of Engineering and Information TechnologyUniversity of New South Wales CanberraCanberraACT 2610Australia Mechanical Engineering DepartmentGlobal College of Engineering and Technology(GCET)P.O.Box 2546 CPO Ruwi 112MuscatSultanate of Oman School of Industrial EngineeringIran University of Science and TechnologyTehran 16846-13114Iran
出 版 物：《Propulsion and Power Research》 (推进与动力（英文）)
年 卷 期：2023年第12卷第1期
页 面：83-103页
核心收录：
学科分类：08[工学] 0825[工学-航空宇航科学与技术]
基 金：University of Guilan, UG Sharif University of Technology, SUT
主 题：Morphing airfoil Lift force Optimization Computational fluid dynamics Micro controller Angle sensor
摘 要：Optimizing flying objects’wing performance has attracted a significant attention in the last few *** this article,some of the main mechanisms for changing the geometry of the wing were investigated and a new mechanism is proposed to improve the aerodynamic performance of the airplane *** designs have been simulated and analyzed from both aerodynamic and control points of *** aerodynamic simulations using CFD methods,two airfoils of NACA series 6 with specifications 65-212 and 65-2012 were *** results indicated that both airfoils used have a better performance compared to others in a certain range of the angle of ***,a new mechanism is proposed to change the wing geometry to optimize its *** the proposed mechanism,the structures of airfoils and wings consist of two fixed and moving parts,which can change their geometry with the help of a control *** fixed part has a grooved track,and as the moving part moves in the direction of the grooves,the curvature of the upper and lower parts of the wing *** design control circuit includes an angle sensor,a micro controller,and a *** CFD results are entered into the micro controller as *** any moment,the micro controller receives the angle data from the angle sensor and by comparing them with the CFD data,and issuing a command to the servomotor,it situates the wing curvature in the optimal state at all *** built mechanism was tested at an attack angle of 0°and 25°.The results showed that the different parts of the mechanism work with very high precision and put the geometric shape of the wing in an optimal state in a completely intelligent *** should be noted that the average error in test for t/c and Xt/c was 15.3% and 9%,respectively.
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