Numerical simulation of the flow field around a cascade of NACA 0012 airfoils-effects of solidity and stagger

In this study, a numerical computation of the flow field around a cascade of NACA 0012 airfoils is carried out. The numerical scheme, using the control volume method, is introduced to solve the governing flow equations. The κ- ε model is employed to take into account the turbulence effects. The grids are generated employing algebraic equations for the boundary point distribution while the Laplace grid generator is employed for the internal point distribution. The trailing edge separation at different angles of attack for solidity ratios and staggers is predicted and the resulting pressure, lift and drag coefficients are computed. It is found that solidity increases the incidence at which maximum lift is obtained and, in this case, a slight increase in drag occurs.