Numerical Experiment of Flow Around a Compound Airfoil

Abstract

Abstract A numerical simulation around a compound airfoil was performed using the vortex method. The compound airfoil consists of a front airfoil, a fixed wing, and a rear airfoil, and it assumes the rudder of a submarine. As for the shape of the front airfoil and the rear airfoil, NACA0012 was used. Reynolds number was Re = 3.8×105. In the numerical simulation, the angle of attack of a front airfoil and a rear airfoil was changed, and the magnitude of the gap between these movable airfoils and the fixed wing was changed. The time history of the fluid force of acting on an airfoil, and the flow pattern were investigated. The total lift was greatly produced, when the front airfoil and rear airfoil attached the same attack angle as the same direction. It was found that the total lift with the large one where the gap between these movable airfoils and the fixed wing is larger can be obtained. It was found that the rear airfoil governs the flow of the compound airfoil.