二元超音速进气道设计与研究  

Design and Study of Two-dimensional Supersonic Projectile Inlet

作　　者：崔立堃[1,2] 李卓[1] 

机构地区：[1]内蒙古工业大学理学院 [2]呼和浩特职业学院,呼和浩特010051

出　　处：《科学技术与工程》2013年第27期8070-8073,8081,共5页Science Technology and Engineering

基　　金：国家自然科学基金(11262014)资助

摘　　要：根据某型超音速弹用冲压发动机进气道的设计要求,综合考虑了诸多因素,设计得到了合理的二元混压式进气道;并基于Fluent平台对其进行了详细的数值模拟。研究了不同攻角对弹体、进气道入口、进气道出口流场的影响。模拟结果表明:随着攻角的增大,由前缘点产生的激波与进气道轴线的夹角变大,进气道入口激波不再交于唇口,进气道内的正激波逐渐靠近唇口,总压恢复系数和流量随攻角的增大均有所下降。Considering the various factors, a proper two-dimensional mixed compression inlet was designed according to the requirements of some supersonic ramjet projectile inlet, and numerical simulation on it was processed by using Fluent software. The effect of attack angle on flow fields of the missile body, the inlet entrance and exit were studied. The results show that the angle between the shock wave generated by the front point and inlet axis became larger, the shock waves didni no longer intersect at the entrance lip, the normal shock wave inside inlet grad- ually closed to the lip, the total pressure recovery coefficient and flow rate were decreased with the attack angle increasing.

关 键 词：超音速进气道 弹用冲压发动机 数值模拟 攻角 

分 类 号：V448.153[航空宇航科学与技术—飞行器设计]