高超弯曲激波二维进气道初步研究  

Preliminary study on hypersonic curved shock two-dimensional inlet

作　　者：张林[1] 张堃元[1] 王磊[1] 南向军[1] 向有志[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2011年第11期2556-2562,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(90916029)

摘　　要：研究了一种压升规律的曲面压缩面,设计了高超弯曲激波二维进气道,并用数值模拟手段对该进气道和同等条件下的常规高超二维三楔进气道、楔+等熵进气道的性能进行了比较.数值模拟表明:通过给定合理压缩面压升规律来设计压缩面并改善压缩面附面层稳定性是可行的,弯曲激波二维进气道的长度比同等条件下的常规二维三楔、楔+等熵进气道分别缩短12%和10%,并且对来流Ma变化不敏感,综合性能优势明显、应用前景大.A type of curved compression surface with certain wall pressure distribution was investigated,and a hypersonic curved shock two-dimensional inlet was designed.The performance was compared through numerical simulation with normal hypersonic three-wedge and wedge-isentropic two-dimensional inlets under the same conditions.The result shows：the curved shock inlet with more stable boundary layer can be designed according a proper wall pressure distribution;the inlet can be shortened by 12% and 10%,respectively,as compared with three-wedge inlet and wedge-isentropic inlet,and is not very sensitive to the change of free stream Mach number;the new inlet has obvious superiority on the overall performance and bright prospect in the applications.

关 键 词：超燃冲压发动机进气道 二维高超声速进气道 压升规律 弯曲激波 数值仿真 

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]