Abstract
Two interacting boundary layers create a three-dimensional separation when fluid flows through a wing. The performance of the airfoil may be negatively impacted by the secondary flow that results from this separation. Up until now, airplanes have frequently used slotted flaps that can avoid separation and lower the resistance value. The current work presents an experimental and numerical investigation into the performance and aerodynamics characteristics of a new single-slotted flap mounted on a Cessna 208b Grand Caravan wing. Numerical simulation using the ANSYS-Commercial CFD package is the approach used herein. A revised Cessna 208b wing with a Grand Caravan single-slotted flap in three flap angles of αF = 0°, 15°, and 30° that researches the performance on its aerodynamics. Ranging from angles of attack α = 0°, 8°, 14°, 16°, and 18°. The fluid used is air, and under conditions of stability, has a cruise speed of 96 m/s at sea level altitude. Observe that a Cessna C208b Grand Caravan aircraft performance and wing's aerodynamic properties will be changed, which has been obtained in the addition of flap angle through simulation. As seen, it can be clearly told that at higher angles of attack with flow separation, because of intensification of turbulence, a higher flap angle may lower the value to 10.20 at αF = 30° and α = 8° at 96 m/s. However, at low angles of attack, the addition of the flap angle at αF = 0° and α = 8° may yield a higher value of CL/CD, amounting to 13.80, which is an indication of better aerodynamic efficiency. The vorticity patterns observed also indicate larger and more dispersed vortices at higher flap angles, contributing to drag buildup and reduced efficiency.