A double wake model for interacting boundary layer methods

In this study a double wake model is presented for an interacting boundary layer method. The model is described initially by employing only to the inviscid flow equations and compared to the aerodynamic design tools that are including the viscous modelling (XFOIL/RFOIL) as well as to the CFD method (SU2) and experimental data on selected airfoils. The details of the implementation of the model into the viscous flow equations are presented. When combined with the integral boundary layer method for the viscous effects, the presented double wake model improves the prediction of pressure distribution as well as the lift coefficients. This is due to the realistic pressure distribution prediction in the separated flows by double wake model. The deficit of interacting boundary layer methods in case of massively separated flows and deep stall regimes can be overcome by use of the proposed double wake model. The improvements in the prediction of the aerodynamic properties of selected airfoils of various thicknesses are shown for both sharp and blunt trailing edges at different operating conditions.