一种两侧布局的无隔道亚声速进气道流场特性

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. 

Flow field characteristics of side-mounted subsonic inlet of the UAV

A side-mounted diverterless subsonic inlet of the UAV(unmanned aerial vehicle) was designed and the flow field was simulated.The design methodology of the bump was presented and the characteristics of the inlet were obtained.The results show that angle of attack and yaw angle have little effect on the inlet's performance within 0°～8°.The total pressure recovery of the inlet is great than 0.965 and the distortion index is less than 0.253 under all states.The inlet meets the requirements of the engine,proving that the side-mounted diverterless subsonic inlet is feasible.It has also been found that there exists a higher pressure region on the bump surface than that on the fuselage for the diverterless subsonic inlet.The effect of pushing boundary layer aside for the bump is related to the fuselage profile,lip,relative positon of the entrance and flight conditions.The leading curve of the bump should not be too sharp for side-mounted inlet and a curved surface is better than a flat one in pushing the boundary layer away.