Numerical studies of side slip effect on stability of airplane with propeller and the high aspect ratio wing

The results of numerical studies of effect of the slip angle (crosswind) on the on stability of airplane with propeller and the high aspect ratio wing are presented. Increase the slip angle from 0 to 20 degrees are change aerodynamic and moments characteristics of airplane due to the deterioration of the power plant and the asymmetric blowing by the pulling propellers. Numerical studies were carried out using the numerical code for the Reynolds-averaged Navier–Stokes equations.