Design of a Flap for Straight Wing of Unmanned Aerial Vehicle

Abstract

In the paper hereby, design of a single stage Fowler flap is proposed. The flap is meant to increase lifting abilities of a straight wing at low speeds. It is applicable to small-sized remotely controlled unmanned aerial vehicles widely available to hobbyists. The design process included thorough analysis of flow around a wing foil in case of both retracted and deployed flap. To obtain aerodynamic coefficients values at different angles of attack and Reynolds numbers was a primary goal. In addition, a linkage mechanism was developed to make it possible for the flap to move along a complex path. Various plots and charts are depicted thereafter with sole purpose of providing better understanding of the idea.