提高固定几何二元进气道低马赫数性能的仿真研究  

Numerical investigation on performance improvement of two-dimensional,fixed-geometry inlet at low Mach numbers

作　　者：骆晓臣[1] 周长省[1] 鞠玉涛[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《推进技术》2010年第4期390-393,共4页Journal of Propulsion Technology

摘　　要：分别以常规低、高马赫数来流设计的固定几何二元混压式进气道为例,采用数值模拟手段,探究了一种改进的外压缩波系配置方案。采用来流马赫数由低到高,外压缩激波依次封口的设计方法,提高了固定几何二元进气道的低马赫数性能。相比常规配波设计的进气道,来流马赫数2.15条件下的流量系数提高了0.07;来流马赫数2.15和2.4条件下,总压恢复提高近0.015。初步研究证明这种设计理念是合理的,该设计方案有待于进一步发展和实验验证。A low and a high design Mach number two-dimensional,fixed-geometry inlet was used,respectively,to investigate the improvement of external compression configurations by the method of numerical simulations.It was designed that the external compression oblique shocks attached the cowl lip in turn while the Mach number of incoming flow varied from low to high.This design enhanced the performance of two-dimensional,fixed-geometry inlet in the lower Mach number range.Contrast to the conventional design inlet,the capture mass flow coefficient has been improved 0.07 at the Mach number of 2.15.The total pressure recovery of inlet has been improved 0.015 around the Mach number of 2.15 and 2.4.The preliminary results show that the design is rational.Further developments remain to be performed on current design.Comprehensive performance of the presented design needs to be validated by experiments.

关 键 词：混压式进气道 数值仿真 内部流动 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]