Calculation of the Civil Aircraft Wing Characteristics in Critical Flight Modes

The article presents key relations of the modified turbulence model, which allows more accurate modelling the separation zones near solid surfaces. The numerical-experimental comparison confirms acceptable quality of the date obtained in the case of flow around the civil aircraft wings. Various approaches to development of the computational code are compared each other and it is shown that, in the case of separation, it is necessary to perform time integration in compliance with stability condition determined using flow core parameters. The comparison of numerical and experimental data shows that modified turbulence model at the critical regime gives result, which better satisfies the experiment.