Numerical Investigation of M21 Aerofoil and Effect of Plain Flapper at Various Angle of Attack

Abstract

Abstract The aerofoil plays an important role in any structure moving in a fluid-like in a passenger plane, jet plane, or helicopter. The aerofoils decide whether the lift force is appropriate to balance the weight of the plane or not and the amount of drag force is required on the vehicle. The purpose of this project is to simulate the M21 Aerofoil with the help of FLUENT and validate it with theory. This Project also includes the study of various Flapper designs and their simulation. Flappers are useful when the Airplane is about to take-off or landing. The Important parameters to be study are Lift Force, Drag Force, lift coefficient, and Drag coefficient. Simulation has been done for the different Angle of Attack which is useful for finding maximum Lift force and Stall Angle. The Work includes simulation of Plain Flapper for the Angle of Attack where CL/CD is maximum. Similar work can be done for different types of Flapper used in Airplane. The stall angle achieved for M21 was 24° and maximum value of CL/CD measured at 7° A.O.A. Investigation also shows that for the 10° plain flap angle highest drag and lift force was possible. It contains the study of the Adverse Yaw effect which rolls the Airplane while taking a turn. since the validity of any theoretical prediction can only be assessed in practice.