摘要
根据现役无人机进气道的结构特点,以后置两侧布局的S弯进气道作为研究对象,完成了一种大偏距、短扩压S弯进气道设计,设计包括中心线、面积变化规律选取以及斜切唇口等;并且对设计模型进行风洞实验研究,得到进气道的速度特性、攻角特性和偏航角特性等。实验结果表明:(1)在大多数实验条件下,进气道具有良好的气动性能,较高的总压恢复(σ>0.986),较低的畸变指数(DC60<0.28);(2)大偏航角状态时,背风侧进气道受机身附面层及机身涡的影响比较大,虽总压恢复系数并不低,但畸变指数DC60较大,在使用中需要采取相应的技术措施。
According to structural features of the active unmanned aerial vehicle （UAV） inlet, a bilateral type S-shaped inlet with large offset and short diffuser is designed. The design includes choosing the inlet center line and area regularity, the beveled lip, and so on. A experiment is conducted in the wind tunnel. In the experiment, the performance of the inlet is obtained, such as the effects on the performance of free stream Mach number, attack angle and yaw angle. Experiments in wind tunnel show that： （1） in most cases, the S-shaped inlet has high total pressure recovery （σ〉0. 986） and low distortion （DC60〈0.28） ; （2） the inlet located at the lee side of fuselage with large yaw angle is greatly influenced by the boundary layer and vortex of the fuselage, so the distortion of the inlet is deteriorated, while the total pressure recovery is quite high.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2008年第2期146-150,共5页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
畸变
实验
两侧式
斜切唇口
S弯进气道
distortion
experiments
bilateral type
beveled lip
S-shaped inlet
