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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。
On the basis of the traditional k-ε turbulence model, the ε equation is abandoned in the near-wall region and replaced by the ε value calculated in the near-wall region according to the resonance three-wave theory model. The two-dimensional wing flow field of NACA0012 A new theoretical model was initially validated and corrected. As a result of noting the dimensionlessness of the theoretical model, the calculation results of the flow field were improved and the Cp distribution more consistent with the experiment was obtained. The analysis in this paper also shows that the effect of inverse pressure gradient on ε is very significant, which verifies the theoretical analysis and the calculated conclusion.