超燃冲压发动机唇口气动热计算研究与分析

采用数值模拟方法,对超燃冲压发动机进气道唇口的气动热进行了计算和分析.依据唇口与前体激波所处相对位置的不同,分三种情形进行了计算研究.结果表明,三种情形下,进气道前缘驻点热流均大于头部.通过算例验证,证明该方法和结论的正确性.研究表明,激波干扰以及前体激波压缩后超声速来流使唇口热流增大,热防护和结构设计时应当予以充分考虑. 

Computation and analysis of aeroheating of scramjet inlet cowl lip

Aeroheating of scramjet inlet cowl lip was investigated using numerical simulation method.Three cases were investigated depending on cowl lip position relative to forebody shock,and computational fluid dynamics(CFD) method was used to calculate blunt bow shock flow and simulate shock/shock interaction flow field.The results were validated with experiments in reference,showing that the inlet leading edge always bears more serious aerothermal challenge than forebody nose.Computation shows that it is shock/shock interaction and compressing supersonic flow post forebody shock that increase cowl lip heat transfer for hypersonic vehicle with airbreathing scramjet.This must be fully considered in the thermal protection and structure design.