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.
Highlights
Rotating missiles produce the Magnus effect during flight [1]
The lateral force of the tail fin was similar to that generated by the angle of attack of 10°; the Magnus moment direction changed with the increase of the angle of attack
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
Summary
Rotating missiles produce the Magnus effect during flight [1]. For nontailed rotor missiles, the asymmetric distortion of the boundary layer and the asymmetric separation of flow in the leeward region are the main causes of the Magnus force [2]. The Magnus moment leads to a coning motion, reduces the missile shooting range, and even causes the flight to fail [5]. For a rotating tail-stabilized missile, the Magnus moment is greatly affected by the altitude, leading to a large-angle conical pendulum movement and greatly affecting the flight stability of the missile. Liu et al [10] analyzed the main reasons for the instability of a certain type of curving tail missile in the Qinghai-Tibet Plateau and put forward an improvement scheme for adopting a straight tail. Ma et al [12] analyzed key differences in the dynamic stability of a rotating missile under plateau and plain conditions and pointed out that the change of the Magnus torque direction was an important factor for the high angle of attack cone pendulum movement of the missile at a high altitude. The transition SST model was adopted in the present work
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