Aerodinamik kanat tasarımının SU2 ile elde edilen 3 boyutlu akış çözümleri ve cevap yüzey yöntemi kullanılarak eniyilemesi

In this study, the aerodynamic shape optimization of a wing is performed by using 3D flow solutions together with response surface methodology. The purpose of this study is to optimize the aerodynamic shape of a wing to achieve the lowest possible drag coefficient while ensuring desired maneuvering capability and lateral stability. Aerodynamic shape optimization is performed for a wing of a turboprop trainer aircraft. Optimization objective and constraints are determined according to mission requirements and the dimensions of turboprop trainer aircraft already operating. Since the objective function and the constraints consist of aerodynamic coefficients, flow solutions are obtained to calculate aerodynamic coefficients by using an open-source RANS solver (SU2). Surrogate models that relate the design parameters to be optimized to the objective function and the constraints are constructed as high-order nonlinear analytical functions with the help of response surface methodology and design of experiment techniques. In the design of the experiment, a sequential experimentation technique is used. The accuracies of the constructed surrogate models are examined to validate the models. Optimization is performed by using the surrogate models validated and the effect of the different optimization algorithms (sequential quadratic programming and interior point) and initial conditions on the optimized wing geometry are examined. Optimized wing geometry is compared with the initial geometry in terms of the objective function value and the suitability of the optimized geometry to the constraints is evaluated.