Analysis of the Magnus Moment Aerodynamic Characteristics of Rotating Missiles at High Altitudes

Abstract

The Magnus moment characteristics of rotating missiles with Mach numbers of 1.3 and 1.5 at different altitudes and angles of attack were numerically simulated based on the transition SST model. It was found that the Magnus moment direction of the missiles changed with the increase of the angle of attack. At a low altitude, with the increase of the angle of attack, the Magnus moment direction changed from positive to negative; however, at high altitudes, with the increase of the angle of attack, the Magnus moment direction changed from positive to negative and then again to positive. The Magnus force direction did not change with the change of the altitude and the angle of attack at low angles of attack; however, it changed with altitude at an angle of attack of 30°. When the angle of attack was 20°, the interference of the tail fin to the lateral force of the missile body was different from that for other angles of attack, leading to an increase of the lateral force of the rear part of the missile body. With the increasing altitude, the position of the boundary layer with a larger thickness of the missile body moved forward, making the lateral force distribution of the missile body even. Consequently, Magnus moments generated by different boundary layer thicknesses at the front and rear of the missile body decreased and the Magnus moment generated by the tail fin became larger. As lateral force directions of the missile body and the tail were opposite, the Magnus moment direction changed noticeably. Under a high angle of attack, the Magnus moment direction of the missile body changed with the increasing altitude. The absolute value of the pitch moment coefficient of the missile body decreased with the increasing altitude.

Investigation of periodic characteristics of perturbed flow over a slender body

“…The asymmetric flow separation occurred over a slender body at a high angle of attack (AoA) [ 1 , 2 ]. In addition, the slender body was the basic geometry of fighter aircraft and missiles, hence, the highly random asymmetric flow was coupled with wings and induces a yawing moment [ 3 ], which was even largely great beyond the control by the rudder of a missile [ 2 , 4 , 5 ]. In addition, the development and bursting of asymmetric vortices were sensitive to the structure of the wings and the coupling position at high AoA [ 6 , [7] , [8] ].…”