Description

The current project simulates Magnetic Force Effect on NACA 0015 airfoil using ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

This airfoil is a symmetrical airfoil that does not produce a lift force at zero attack angle. We investigate the lift coefficient of this airfoil at different attack angles with and without Magnetic Hydro-Dynamic (MHD).

In this problem, we study the separation and the maximum angle of attack where the separation does not occur. By applying the magnetic force (MHD), the separation happens at a larger angle of attack.

We have designed the present 2-D geometry by Design Modeler software. Also, an unstructured triangular mesh has been applied around the airfoil using ANSYS Meshing software.

Magnetic Force Methodology

In this project, we aim to investigate the magnetic field effect in the computational zone. We have enabled the MHD module in fluent software to consider the magnetic force effect on the flow.

Magnetic Force Conclusion

This project provides velocity and pressure counters, streamlines, and velocity vectors after applying the plasma actuator. As can be seen from the velocity contour, the plasma actuator’s application causes the flow in the boundary layer to accelerate and adhere to the surface of the airfoil.

Also, the leading edge pressure suction has increased, and as a result, the lift has increased. As it turns out, after applying the plasma actuator, the flow separates from the airfoil surface somewhere before the initial separation point, which means the separation is delayed.

Therefore, it can be concluded that by applying a plasma actuator (MHD) to the NACA 0015 airfoil; a static stall occurs at a larger angle of attack.