Numerical simulation of the aerodynamic characteristics of the NACA 0018 airfoil at medium range Reynolds number

In the present work, simulations of the flow around the NACA 0018 airfoil operating at Reynolds number 7 X 10(5) are performed using the EasyCFD software package. The influence of the advection scheme and turbulence model on the computed lift, drag and momentum coefficients is presented and an evaluation of the obtained results is made by comparison with published experimental data. It is concluded that predictions agree very well with experimental data up to 18 degrees angle of attack, when using the SST turbulence model with the second order advection scheme. Limitations of simulations are shown when the airfoil operates at larger angles of attack, where unsteady periodic flow is verified. The turbulence model and the advection scheme affects both lift and drag values, but to a larger extent for drag. Predictions at high angles of attack overestimate both lift and drag coefficients, but underestimate the momentum coefficient.