Numerical Analysis of NACA 0012 Airfoil Lift and Drag Coefficient

Abstract

The NACA four-digit classification system defines airfoil geometry through a four-part code. Maximum camber (first digit, % of chord), camber position (second digit, tenths of chord), and maximum thickness (last two digits, % of chord) are specified. Notably, a 12% maximum thickness indicates a symmetric airfoil profile with no camber. This study examines the aerodynamic performance of a NACA 0012 airfoil under subsonic flow conditions. We analyze the behavior of the airfoil in terms of the lift it produces as a result of air attacking it. We calculate lift against a C-type geometry. The mathematical model considers varying angles of attack for values of inlet velocity. The mathematical model includes the Nervier-Stokes equations and the Standard k turbulence model to capture the turbulence. The model involves solving a set of nonlinear partial equations and differential equations simultaneously. The finite volume method serves as the solver for this task. ANSYS Workbench 16.2 includes FLUENT for solving all simulations.