Investigation of the effects of angle of attack and tail deflection angle on the controlling tail flow field

摘要

In the current study, the flow behavior due to the variation of the tail angle of attack and its deflection has been investigated on a body-tail with a controlling tail. Numerical computations were carried out at a constant velocity of 90 m/s with the tail angle of attack and deflection ranging from 0 to 30 degrees. It provides a deeper understanding of how the aerodynamics of the tail is influenced by the deflection of the tail and the variation of the angle of attack, along with body and nose vortices. The formation of structure and breakdown of vortices along with their effects on the pressure distribution over the tail and the corresponding normal force coefficients derived from the numerical results. As a result, due to increasing the angle of attack or the deflection angle, the high-pressure area extends over the surface of the controlling tail facing the flow. Besides, the effects of angles of attack on the normal force coefficients on the tail are more than deflection angles due to body effects and the corresponding generated vortices. A comparison of numerical results and experimental tests showed satisfying accuracy and provided reliable details on the flow behavior and the highest calculated error rate was 12.8%.