Numerical and Experimental Study of Winglet Effect with Different Cant Angles

Abstract

The present work aims to investigate the aerodynamic characteristics of the winglet cant angle of Boeing 737-800 wing numerically and experimentally. The wing contain two swept angles 38.3^o and 29.13^o respectively, taper ratio 0.15 and aspect ratio 8.04. The wing involves three types of airfoils sections. Four cant angles for blended winglet have been considered (0^o, 34^o, 60^o, 83.3^o). The winglet has been analyzed to find the best cant angle for the wing without and with winglet. These models have been tested theoretically at Reynolds number of 2.06 x10⁶ in order to study the winglet aerodynamic characteristics which consist of coefficient of Drag, coefficient of lift and Lift to drag ratio, pitching moment coefficient and bending moment coefficient for (0^o, 2^o, 4^o, 6^o, 8^o, 10^o) angles of attack. SOLIDWORK 2016 software, was used to design the geometry of the wing and winglet. ANSYS FLUENT 17.0 in three dimensions with (k - ε) turbulent model was used to solve the governing equations. The experimental tests were carried out in an open low subsonic wind tunnel of 70cm × 70cm ×150cm test section at Reynolds number of 4.33 x10⁵. The experimental lift, drag forces and pitching moment measurement were considered by three component balance device at different angles of attack. The results show that 34^o cant angle is the best angle, at which 2-3% increase in lift coefficient, 2-3.9% decrease in drag coefficient, 3.5-6% increase in pitching moment coefficient and 3-6.6% increase in lift to drag coefficient by using blended winglet. Good agreement between the experimental and computational results are shown.