Adjoint Based Optimization of NACA 4412 Airfoil

In this research paper, the shape optimization of the NACA 4412 airfoil has been carried out at 0
⁰
angle of attack and stall angle of attack, at moderate Reynolds number. The NACA 4412 airfoil has been used in sports planes which have a higher cruise speed compared to cargo planes. Hence, the shape of the airfoil needs to be optimized for achieving a higher lift to drag ratio. The adjoint method has been used to optimize the shape using ANSYS Fluent software.