摘要
通过改变中心体形状,设计了新型轴对称基准流场,可显著降低反射激波强度,明显提高压缩效率。基于该基准流场和传统基准流场,分别设计了两个圆形出口内收缩进气道,并对二者的流场及总体性能进行了数值研究。结果表明,新的进气道设计点和接力点肩点附近激波附面层相互作用减弱,流场结构优于传统进气道,压缩效率明显提高,同时进气道起动性能得到改善。
An innovative basic flowfield is designed and studied by using a controlled centre body to weak the reflection shock wave and increase the compression efficiency.Two circular inward turning inlets with new and old basic flowfileds are designed and numerically studied.The results indicate,compared with the old inlet,the new one has weaker cowl shock wave/boundary layer interaction,better flowfield,higher compression efficiency,and better start performance.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2012年第2期254-259,共6页
Journal of Astronautics
基金
国家自然科学基金(90916029)
关键词
高超内收缩进气道
基准流场
数值模拟
Hypersonic inward turning inlets
Basic flowfield
Numerical simulation
