摘要
在传统的k-ε湍流模型基础上,在近壁区放弃求解ε方程而代之以根据共振三波理论模型在近壁区系统计算的ε值构成封闭,通过对NACA0012二维翼形流场的计算,初步验证并适当修正了新的理论模型,由于注意到了理论模型计算结果的无量纲性,从而改善了该流场的计算结果,得到了与实验更为相符的Cp分布。本文的分析还表明,逆压力梯度对ε的影响非常显著,验证了理论分析和计算得到的结论。
Based on the classic k-Ε turbulence model, Ε equation is replaced by a theoretical model which formed a near-wall turbulence model. The calculation of the 2-D NACA0012 airfoil in low Reynolds number flow field validated the theoretical model. The non-dimensional property of the result obtained from the theoretical model improves the calculation, so the distribution of Cp agrees better with experimentation. The analysis shows that the effect of converse pressure gradient on Ε is prominent, and it validates the result of theoretical and numerical computation.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第2期177-181,共5页
Journal of Aerospace Power
基金
国家自然科学基金资助项目(10172016
50476004)
国家自然科学基金重点基金资助项目(50136010)
关键词
航空、航天推进系统
湍流
理论模型
近壁区
Aircraft propulsion
Airfoils
Mathematical models
Reynolds number
Spacecraft propulsion
