摘要
从雷诺平均的非定常Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程出发，利用时间相关法，采用隐式的ＢｅａｍＷａｒｍｉｎｇ格式中的矢通量分裂技术，结合Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型，数值模拟了收敛喷管的内流场和喷射流场。通过对超临界工况下喷管跨音速流场的数值计算，表明本文的结果与试验结果是吻合的。
The internal flow field and the flow jet field in a convergent nozzle are simulated based on Renolds-average unsteady Navier-Stokes equations, with time-dependent method, flux vector splitting technique in implicit Beam-Warming scheme and Baldwin-Lomax algebraical turbulent model. A transonic flow field in a nozzle under supercritical operation condition is numerically computated, which demonstrates that the results in this paper are in good agreement with experimental data.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1994年第3期14-20,共7页
Journal of Propulsion Technology
关键词
喷管气流
湍流射流
数值模拟
Navier-Stokes equation
Nozzle gas flow
Turbulent jet
Flow distribution
Numerical simulation
Numerical calculation
