Description

In this project, steady airflow over a flapped airfoil with an attack angle equal to 12 degrees is investigated by ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

The present model is designed in two dimensions using Design Modeler software. The meshing of the model has been done using ANSYS Meshing software. The element number is 64731.

Flap Methodology

A flap is a high-lift device used to reduce the stalling speed of an aircraft wing. Flaps are usually mounted on the wing trailing edges of a fixed-wing aircraft. Flaps also cause an increase in drag, so they are retracted when not needed.

This project investigates steady airflow over a flapped airfoil with an attack angle of 12 degrees. The air enters the domain with a velocity magnitude of 45m/s and passes over the airfoil.

To capture the flow patterns near the airfoil's surface and to calculate drag and lift forces precisely, the SST k-omega model is used.

Flap Conclusion

At the end of the solution process, two-dimensional contours related to the velocity, pressure, and turbulent viscosity inside the domain are obtained. The contours related to pressure clearly show how the pressure difference between the pressure and suction sides of the airfoil can contribute to the generation of lift force.

Also, the stagnation point in the leading edge can be observed. Furthermore, the wake region is conspicuously observable in the velocity and turbulent viscosity contour.

In addition, based on the calculated values for lift and drag forces, The lift coefficient of an airfoil with and without the flap is equal to 1.2182 and 1.0530, which shows the effectiveness of the flap in aerodynamic lift force generation.

Moreover, the drag coefficient of the airfoil in the presence of a flap is equal to -0.0273, which is less than airfoil without a flap, where the drag coefficient is equal to -0.0822, which proves that flap presence is effective in drag force reduction that is favorable in aerodynamics applications.