عنوان مقاله [English]
A series of experiments are conducted to study the velocity field around a wing-canard body that represents a highly maneuverable aircraft. All experiments were conducted in a subsonic wind tunnel under two different angles of attack,لmodel=15, 20 degrees, while the canard angle of attack varied between -10 to 10 degrees. The data shows that, at all the angles of attack mentioned before, the canard downwash passes over the main wing surface, which results in a reduction of the pressure over the wing surface. These phenomena delay the model stall angle of attack, hence, increasing the performance of the model. Furthermore, to reduce the experiments, a neural network system was used, which is capable of both prediction and extrapolation. The neural network data shows both canard and main wing vortices at various stations over the wing surface. As the canard angle of attack increases, its corresponding vortices become stronger and cover a layer portion of the wing surface. As a result of this vortex system, the pressure over the wing surface drops considerably.