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对一种两侧翼下布局的无人机无隔道亚声速进气道进行了气动设计和数值模拟研究,给出了该进气道的鼓包结构设计思想,得到了设计飞行马赫数下该进气道的工作特性.计算结果表明:在0°～8°范围内,攻角和侧滑角对进气道性能影响不大,在所有计算状态下,该进气道的总压恢复系数大于0.965,畸变指标小于0.253,满足发动机的工作要求.研究发现:无隔道亚声速进气道的鼓包表面存在相对于机身较高的压力分布,鼓包排除附面层的效果与机身形状、唇口、进口位置以及飞行姿态等有关,对两侧布局方案,鼓包头部不宜太尖,曲面机身有利于附面层的排移.
The aerodynamic design and numerical simulation of a UAV without duct under the wing are carried out. The design idea of the structure of the air intake is given. The results show that in the range of 0 ° ~ 8 °, the angle of attack and the side slip angle have little effect on the inlet performance, and the total pressure recovery coefficient of the inlet is greater than 0.965, the distortion index is less than 0.253 to meet the engine’s work requirements. The study found that there is a relatively high pressure distribution on the surface of the drum without duct sub-sonic intake duct, Lip position, import location and flight attitude, etc., on both sides of the layout program, drum head should not be too sharp, curved body is conducive to the displacement of the attached layer.