IMPROVEMENT OF AERODYNAMIC PERFORMANCE OF AN AIRCRAFT USING MORPHING WING

Authors : İbrahim GÖV, Mehmet Hanifi DOĞRU, Ümit KORKMAZ

Pages : 23-37

View : 57 | Download : 8

Publication Date : 2021-10-31

Article Type : Research Paper

Abstract :The aerodynamic performance of an aircraft directly affects the operating cost of the aircraft. The aerodynamic performance can be defined as the Cl/Cd ratio. To decrease operating cost Cl/Cd ratio must be increased. The main factor affecting the Cl/Cd ratio is the airfoil. Hence in this study, focused on a morphing airfoil during the flight to obtain maximum Cl/Cd ratio at a various angle of attack values. 2D CFD analysis is used in this study based on NACA63-215 airfoil and a new NACA36-215_1 airfoil which is modified NACA63-215. In analyses Cl/Cd ratio and flow separation were investigated as the performance parameters. At the end of the study, it was seen that the NACA63-215 airfoil should be used between 110-170 angle of attack, NACA63-215_1 should be used between 00-100, 180-230 angle of attack, to obtain maximum performance.
Keywords : Morphing Airfoil, flow separation, lift coefficient, drag coefficient

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