Further comparisons of interactive boundary-layer and thin-layer Navier-Stokes procedures

Calculations of the flows over NACA 4412 and GA(W)-2 airfoils with low-speed flow and over NACA 0012 and RAE 2822 airfoils with transonic flow are reported. They were obtained by solving potential flow and boundary-layer equations, and by solving thin-layer Navier-Stokes equations. The results cover a range of angles of attack up to and including stall and allow the evaluation of the numerical and physical features of the two solution methods. The agreement with measurements is acceptable except between the results of the thin Navier-Stokes equations and measurements in subsonic flow at high angles of attack. The interactive boundary-layer method is considerably more efficient requiring considerably less computer time and storage.