Aerodynamic Effects of Designing A Suction Channel Over NACA 4412 Wing

Abstract

In this study, a wing is designed by using NACA 4412 profile and computational numerical analysis is discussed with suction method.First of all, the 3D wing is designed with the SolidWorks and the numerical study of this designed wing is carried out using ANSYSFluent, a famous CFD (i.e. Computational Fluid Dynamics) software. It is based upon finite volume method approach. Two differentconfigurations are used for numerical study. The first of these configurations is the $S_1$, which represents the initial state of the wing; $S_2$refers to the wing design with suction channel. The straight flight angle of attack of the wing is 6 degree and the flow separations overthe wing, which occurred in 25% of the wing chord length, are calculated at this angle of attack by the numerical study. At this point ofchord length, a venturi channel is formed which initial point is the upper surface of the wing and throughout the inner part and finallymeets with air from the trailing edge. The main purpose of this channel is to decrease the force at the place where the flow begins todeteriorate during the flight and to increase the aerodynamic performance. In order to be able to examine the change in aerodynamic performance, the lift and drag coefficient values on the wing are obtained in 10 angles of attack (i.e. -6, -4, -2, 0, 2, 4, 6, 8, 10, 12)separately for both configurations. These coefficients obtained for S1 and $S_2$ configurations are compared with each other. In thisnumerical study based on the comparison results, it is found that there is a significant increase in the performance of $S_2$ configurationcompared to the $S_1$ configuration.