CFD APPLIED TO THE SIMULATIONS OF THE ANGLE OF ATTACK AND FLUTTER DERIVATIVES OF AN AIRFOIL NACA0012

Resumo

This paper presents a study of the aerodynamic behavior of a NACA0012 airfoil modeled in two dimensions
using computational fluid dynamics. In the first analysis, the aerodynamic lift and drag coefficients were obtained
for a range of angles of attack for Reynolds number equal to 700000. The kωSST turbulence model was employed,
and the model has no displacement. The second analysis lies in the identification of the flutter derivatives in
motion-related fluid forces exerted on an airfoil, with Reynolds number equal to 800. The methodology is based
on the idea proposed by Le Maıtre et al. [1], which assumes a linear relationship between force functions and the
laws of motion of the airfoil so that superposition in both frequency and freedom spaces is allowed. To obtain
the flutter derivatives a known sinusoidal vibrations were applied in the airfoil mid-chord. With the response
of these coefficients and using Fourier transforms for the treatment of their signals, the flutter derivatives are
subsequently calculated. A numerical model to solve the incompressible Navier-Stokes equations is proposed
using the OpenFOAM CFD free code. The results from both sets of the simulation were compared with those from
the literature, validating the numerical models.