IMPROVEMENT OF AERODYNAMIC PERFORMANCE OF AN AIRCRAFT USING MORPHING WING

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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