摘要
本文分析了单相流和两相流通过喷管实现超音速流动的过程，建立数学模型并求解了两相流动在流道内加速至超音速的过程和超音速两相流动产生激波前后的热力学参数，得出了两相流动激波前后在不同升压比下参数的变化，两相流动激波前后的最高升压比与波前马赫数的关系式，分析了激波前后的熵产和 损。
A mathematical model describing the pressure jUmP by shock wave has been proposed.Parameters after the shock are given Under ddeeat pressure rise ratio. The pressure rise ratio for the shock wave is greatly influenced by the condensation quality after the shock. The maXham pressure rise ratio shows an approximate linear relation with the square of MaCh number before the shock. The elltropy production and awilability destruction after the shock are also analyzed.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2001年第3期284-286,共3页
Journal of Engineering Thermophysics
基金
自然科学基金(No.59876045)
国家重点基础研究发展规划项目(No.G200026305)
关键词
汽液两相流
超音速
热力学分析
激波
twesphase flow
supersonic
shock wave
eotropy analysis
