Comparative numerical investigations on aerodynamic performance of plain flaps using CFD for fixed-wing UAVs

Abstract

Fixed Wing UAVs (Unmanned Aerial Vehicles) have been emerged in the execution of medium and large range based dangerous applications. But few of the researches were only dealt the aerodynamic perspective investigations on Fixed Wing UAVs. Therefore, this paper presents the study of aerodynamic performance about NACA 4415 aerofoil with and without flaps of the Fixed Wing UAVs. The design of aerofoil with plain flaps requires a better understanding of the aerodynamics changes of the coefficient of lift. The aerodynamic properties, including lift coefficients, drag coefficients, and lift-to-drag ratio were measured and analyzed for detailed investigations. Aerofoil with and without flaps of different angles of attack of lift and drag curves were reported for comparison. Simulation tests were conducted on a cambered aerofoil with and without flaps of different angles of attack. Analyses are made in Fluent with laminar flow velocity 15 m/s for NACA 4415 at Reynolds number 1×106. The coefficient of lift is increased in acceptable amount in NACA 4415 aerofoil with plain flaps while comparing the NACA 4415 aerofoil without plain flaps.