不可压缩机翼绕流的有限谱法计算

结合有限谱QUICK格式求解不可压缩粘性流问题。这一格式用于模拟不同攻角下的NACA1200机翼绕流问题。利用体积力，提出了将流场速度从0加速到来流速度的方法。区别于传统的压力梯度为零的边界条件，推导出一个更精确的压力边界条件。为使速度散度保持为零，在泊松方程中给速度散度一个特殊的处理。这一成果说明了有限谱法不但具有很高的精度，而且能灵活地和其他格式一起构造出新的格式，从而成功地应用到复杂流场不可压缩流动的数值计算中。

Finite spectral computation of incompressible flows around airfoil

Finite Spectral QUICK scheme is developed to calculate incompressible viscous flows.This scheme is used to simulate the flows around NACA1200 airfoil at different angles of attack.In terms of body forces,a method of accelerating the flow velocity from 0 to freestream velocity in proposed.In contract to the conventional boundary condition with zero pressure gradient,an accurate formula for boundary condition of pressure is derived.In order to keep the divergence of velocity being zero,a special treatment of divergence term in Poisson equation is proposed.This application indicates that finite spectral method possesses not only high accuracy but also high flexibility for complex incompressible flow problems.