非均匀来流下等压力梯度曲面压缩二维进气道性能  

The Performance of Constant Pressure Gradient Curved Compression 2-D Inlet Under Non uniform Inflow

作　　者：潘瑾[1] 金峰[2] 张堃元[2] 

机构地区：[1]江苏海事职业技术学院,南京211170 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《工程热物理学报》2015年第10期2137-2141,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.90916029)

摘　　要：本文选用性能较好的设计点马赫6三楔压缩二维进气道为基准模型,精心设计了设计点马赫6性能与基准模型相当,采用等压力梯度曲面压缩的二维进气道。数值模拟分析了两进气道在非设计点和非均匀来流下的流场和性能。结果表明:非设计点,采用等压力梯度曲面压缩二维进气道,其流量系数、总压恢复和压比均高于三楔压缩二维进气道;在非均匀来流下,采用等压力梯度曲面压缩二维进气道比基准进气道性能要好,低马赫数下起动性能也较好,值得进一步研究。The well-designed constant pressure gradient curved compression 2D inlet model at design point Mach number 6 was conducted,and the inlet performance is similar with a three wedges compression 2D inlet at design point Mach number 6.The two inlets flow fields and performance in uniform and non-uniform inflow are discussed by using numerical simulation.The results show that,at off-design point Mach number,the curved compression 2D inlet model gets a higher mass capture ratio,total pressure recovery and pressure ratio;in non-uniform inflow,the curved compression 2D inlet model is of better performance and easy starting in lower Mach number inflow.So further investigation will be continued.

关 键 词：超声速进气道 曲面压缩 等压力梯度 弯曲激波 

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]