Numerical and experimental study of the aerodynamics of a civil-aircraft model at high angles of attack and during rotation

A numerical and experimental study of the flow near a standard civil-aircraft model at high angles of attack in the range from 0 to 90 degrees and at subsonic velocities of the oncoming flow has been carried out. The experiments were performed in the T-105 wind tunnel of TsAGI. The calculations were carried out within the framework of solving the Reynolds-averaged Navier-Stokes equations. A comparison of the calculated and experimental integral characteristics showed a good agreement with an accuracy sufficient for practice. Physical features of the flow and their influence on the aerodynamic characteristics of a stationary model at high angles of attack, as well as in the regime of rotation of the model with a constant angular velocity, are revealed.