唇缘钝化对高超声速进气道气动特性影响的数值研究  

Investigation on aerodynamic characteristics of hypersonic intake with blunted cowl-lip

作　　者：温邻君 张旭[2] 

机构地区：[1]国家知识产权局专利局专利审查协作河南中心,郑州450002 [2]中国燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2015年第1期7-13,共7页Gas Turbine Experiment and Research

摘　　要：采用二维数值模拟方法,详细探讨了高超声速飞行条件下唇缘钝化对进气道气动特性的影响,给出了唇缘钝化前后进气道在设计与非设计状态下的气动特性。研究表明:唇缘钝化使进气道流场显著复杂化,恶化了进气道气动性能,降低了进气道抵抗出口反压干扰的能力。通常情况下,随着钝化半径的增大,进气道的流量捕获小幅上升,出口马赫数、总压恢复系数下降;在激波相干结构强烈作用时,进气道出口马赫数和总压恢复系数随钝化半径的增大呈现非单调性变化。本研究可为进气道构型的二次设计提供指导。At hypersonic flight conditions, the sharp cowl-lip leading edge must be blunted because of se？vere aerodynamic heating. The effects of cowl-lip bluntness on aerodynamic characteristics of hypersonic intake were researched using two-dimensional numerical simulation. At a wide range of operation condi？tion, flow characteristics and performance of hypersonic intake with or without blunted cowl-lip were ob？tained to direct the secondary modification of hypersonic intake configuration. Results showed that cowl-lip bluntness made the internal flow-field complex, deteriorated the intake performance, and weakened the ability of holding shock interference. The mass-capture of intake increases with the increase of blunted cowl-lip radius while Mach number and total pressure recovery at the exit reduces remarkably. From the oc？currence of shock interference pattern, it can be noted that Mach number and total pressure recovery at the exit presents a non-monotonic variation with the increase of blunted cowl-lip radius.

关 键 词：超燃冲压发动机 钝化唇缘 高超声速进气道 激波相干 气动特性 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]