Numerical and Statistical Aerodynamic Performance Analysis of NACA0009 and NACA4415 Airfoils

In this numerical and statistical study, lift drag coefficient performances of NACA-0009 NACA-4415 airfoils were evaluated in accordance with various attack angle at constant velocity wind. Lift coefficients was numerically determined by computational fluid dynamics code ANSYS FLUENT. Analysis design calculations implemented using L16 orthogonal array based on Taguchi method. Angles airfoil types considered as control factors. The optimum level effect each factor responses statistically analyses Signal-to-Noise ratio variance. As a result maximum minimum achieved NACA4415 compared to NACA0009 airfoil. increase the leads for both airfoils.