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针对某超声速飞行器,采用数值模拟方法研究了不同弦向缝隙下机翼与后缘舵之间的绕流特性,在兼顾亚声速气动特性的基础上获得了缝隙对舵效及气动性能的影响规律。结果表明,亚声速时舵效随缝隙的增大降低较多;超声速时缝隙对舵效的影响较亚声速小,当缝隙为10 mm时飞行器的舵效及气动性能最优,研究结果可为超声速飞行器后缘舵设计提供定性的参考依据。
Aiming at some supersonic aircraft, the numerical simulation method was used to study the flow around the wing and the rear edge under different chordwise gaps, and the influence of the gap on the rudder efficiency and aerodynamic performance was obtained based on the subsonic aerodynamic characteristics . The results show that the rudder efficiency decreases with the increase of the gap at subsonic speeds. The effect of the supersonic speed on the rudder efficiency is smaller than that of the subsonic speed. When the gap is 10 mm, the rudder effect and aerodynamic performance of the aircraft are optimal. The supersonic aircraft rear edge helm design provides a qualitative reference.