A vortex panel method is presented to simulate low speed inviscid separated flow past an airfoil with a spoiler.
本文介绍用涡面元法模拟带扰流片的翼型低速无粘分离绕流。
The method is based on the second-order or third-order geometric panel and vortex singularities.
面元和奇点的分布分别采用了二阶和三阶的形式。
The method is based on the second-order or third-order geometric panel and vortex singularities.
面元和奇点的分布分别采用了二阶和三阶的形式。
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