XFOIL: An Analysis and Design System for Low Reynolds Number Airfoils
XFOIL: An Analysis and Design System for Low Reynolds Number Airfoils
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DOI：
10.1007/978-3-642-84010-4_1
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发表时间：
1989
期刊：
影响因子：
--
通讯作者：
M. Drela
中科院分区：
文献类型：
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作者：
M. Drela
介绍了亚临界翼型粘性/无粘性分析和混合反设计的计算方法。本文发展了一种适用于直接和混合逆模态的带Karman-Tsien压缩性修正的无粘线涡面元方法。叠加在翼型和尾流上的源分布允许模拟粘性层对势流的影响。粘性层采用两方程滞后耗散积分法。层流和湍流层处理，与e9型放大配方确定的转折点。边界层和转捩方程与无粘流场用整体牛顿法同时求解。该方法特别适用于含过渡分离泡的低雷诺数翼型流动的快速分析。计算了表面压力分布和整个极性，并与实验数据进行了比较。设计过程中的例子。
Calculation procedures for viscous/inviscid analysis and mixed-inverse design of sub critical airfoils are presented. An inviscid linear-vorticity panel method with a Karman-Tsien compressiblity correction is developed for direct and mixed-inverse modes. Source distributions superimposed on the airfoil and wake permit modeling of viscous layer influence on the potential flow. A two-equation lagged dissipation integral method is used to represent the viscous layers. Both laminar and turbulent layers are treated, with an e9-type amplification formulation determinining the transition point. The boundary layer and transition equations are solved simultaneously with the inviscid flowfield by a global Newton method. The procedure is especially suitable for rapid analysis of low Reynolds number airfoil flows with transitional separation bubbles. Surface pressure distributions and entire polars are calculated and compared with experimental data. Design procedure examples are also presented.