Self-Actuating Flap for Fixed Wing Micro Air Vehicle
Present computational investigations have been performed to study the effect of a fixed flap on the performance of airfoil at low Reynolds number. The flap is fixed at two locations (0.7c, 0.8c) with three deployment angle (30°,45°,60°) on the suction surface of the airfoil. Here flap is used as lift enhancing effectors. All the computational analyses have been carried out via ANSYS V14.5 package (Fluent, Workbench 14.5). It has been found before the stall angle, the lift coefficient for the airfoil with the flap is lower than the clean airfoil and after the stall point, all the flap configuration airfoils improve the lift coefficient and stall angle of attack. For flap locations at 0.7c and υ = 30°, CLmax increases from 1.1 to 1.23 and αstall increases from 12° to 16°. Initially drag coefficient is less for the clean airfoil, but after stall point, it becomes high than flapped airfoil.