IMPROVEMENT OF AERODYNAMIC PERFORMANCE OF AN AIRCRAFT USING MORPHING WING

Year 2021, Volume: 6 Issue: 2, 23 - 37, 31.10.2021

İbrahim Göv , Mehmet Hanifi Doğru , Ümit Korkmaz

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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