Adjoint based aerodynamic design optimization of airfoil and wing twist

In this study, two-dimensional and three-dimensional aerodynamic design optimizations are performed with SU2 open-source CFD code for an air vehicle regarding lift coefficient, drag coefficient, moment coefficient, and thickness to chord ratio. SU2 optimization cycle is used for the optimization studies including Scipy library. Aerodynamic coefficients and gradients are the input parameters for the sequential least squares quadratic programming optimization algorithm. Gradients of the objective and constraint functions are obtained with adjoint solver of the SU2. Hicks-Henne bump functions are used to parametrize the airfoil. Free Form Deformation box is used to parametrize the wing geometry. In airfoil optimization study, a maneuevering and a high speed contitions are chosen for a basic trainer aircraft to perform multipoint optimization. For these optimization conditions, baseline lift coefficients are defined as the equality constraint function of the baseline airfoil. Moment coefficient and thickness to chord ratio are defined as the inequality constraint function and drag coefficient is defined as the objective function. In three-dimensional study, twist angle optimization is performed for a basic trainer aircraft. Lift to drag ratio is defined as the objective function. Also, twist angle optimization is performed for Onera M6 wing in transonic flow conditions with Euler flow solver. Lift coefficient is defined as the equality function and drag coefficient is defined as the objective function.