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本文介绍机翼跨音速定常无粘绕流的一种数值计算方法。选用精确速势方程作为问题的数学模型。在直角坐标系中,经过适当的坐标变换,先把后掠翼变成矩形翼,再把无限的物理空间变成有限的计算空间。在计算空间中,用有限差分格式(亚音速区用中心差分,超音速区用旋转差分)对精确速势方程离散化。差分方程形成的代数方程组用线松弛迭代求解。
In this paper, we introduce a numerical method for the steady non-viscous flow around a transonic wing. Use the exact velocity equation as a mathematical model of the problem. In Cartesian coordinates, after the appropriate coordinate transformation, the first swept wing into a rectangular wing, then the infinite physical space into a limited computational space. In the computational space, the exact velocity equations are discretized using the finite difference format (center difference for subsonic region, rotational difference for supersonic region). Algebraic equations formed by difference equations are solved by a line relaxation iteration.