摘要
对大面积比超音速扩压器引射系统中的扩压器部分进行分析研究。根据扩压器引射系统流动模型建立引射理论，并通过与试验结果相对比，提出扩压器工程设计的有效方法。并编制了计算机程序进行设计计算。利用大面积比超音速扩压器系统的设计方法，可以进一步提高火箭发动机高空模拟试验的模拟高度，进行多种发动机高空模拟试验。
An engineering method for designing large-area-ratio supersonic diffusers was provided in this paper. The model of ejector flow was deduced from experimental observations. Based on the comparison of theory with experimental results an optimal designing method for large-area-ratio diffuser is accomplished. Serious computer programs were designed. The computation of diffuser performances are also programmed.Using this designing method the altitude simulated experimentally for various rocket engines can be improved.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第5期28-33,共6页
Journal of Propulsion Technology
关键词
火箭发动机
超音速扩压器
高空模拟试验
喷管
Rocket engine, Supersonic diffuser, Altitude simulation test, One dimensional flow
