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本文提出一种新的跨音速有粘-无粘干扰迭代的算法。 外流计算利用文献[1]提出的一种快速算法。粘流(附面层)用Cebeci-Smith盒式法,湍流用简单的代数旋涡粘性模型描述。跨音速有粘-无粘迭代是以位移厚度为迭代参数,不断迭代直至收敛。 本文对零攻角无分离NACA0012翼型进行了计算,结果与实验吻合得比较满意,且收敛快,数值稳定,可期在实中得到应用。
In this paper, a new iterative algorithm with trans-viscous and non-stick interference is proposed. Outflow calculation uses a fast algorithm proposed in [1]. The viscous flow (topcoat) is described by the Cebeci-Smith cassette method with turbulent flow using a simple algebraic vortex viscosity model. Acoustic-viscous-non-stick iteration is the displacement of the thickness of the iteration parameters, continuous iteration until convergence. In this paper, the zero-angle-of-attack non-separation NACA0012 airfoil is calculated. The results are in good agreement with the experimental results, and the convergence is fast and the numerical value is stable.