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Airfoil is the cross-section shape of wing which generates a significant magnitude of lift force in an airflow, it is the most important part of an aircraft. In this study a geometrical twisted wing configuration is designed using different airfoils in which NACA 23012 is used at tip of the wing, NACA 23015 is used at mid span and NACA 23018 is used at the root of the wing. ANSYS is used for the creation of geometry and meshing and FLUENT is used as a solver to numerically analysis the airfoils of wing configuration. The aerodynamic performance parameter of the wing is estimated using the turbulence model.

Numerical Analysis and Estimation of Aerodynamic Performance of a Geometric Twisted Wing Configuration using NACA 23012, NACA 23015 and NACA 23018