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本文将跨音速定常小扰动势流混合差分法推广到跨音速大扰动定常势流,提出了在局部速度坐标系中求解跨音速精确势流方程的插值混合差分法。作为算例,计算了双圆弧翼型和NACA0015翼型对称问题压力分布,并与已知实验值和双圆弧翼型小扰动混合差分法计算值进行比较,结果接近。试算表明,本文提出的插值混合差分格式是稳定和收敛的。本文解决了M_∞趋近于1的计算难点。
In this paper, the hybrid difference method with transonic steady-state perturbation potential flow is generalized to the transonic steady-state flow with large perturbation. An interpolation mixed difference method is proposed to solve the exact transonic potential flow equation in local velocity coordinate system. As an example, the pressure distributions of the double-arc airfoil and the NACA0015 airfoil symmetric problem are calculated and compared with the known experimental values and the double-airfoil small perturbation mixed difference method, the results are close. Trial calculations show that the proposed interpolation hybrid difference scheme is stable and convergent. This paper solves the computational difficulty that M_∞ approaches 1.