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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >A Method of Calculating Inviscid Flow around Arbitrary Airfoils in Upstream Shear
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A Method of Calculating Inviscid Flow around Arbitrary Airfoils in Upstream Shear

机译：一种计算上游剪切机翼周围无粘性流的方法

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摘要

In this method the inviscid flow field is decomposed into two parts: a known field with constant vorticity representing the upstream shear and an unknown irrotational field representing the disturbance flow caused by the airfoil. The unknown field is handled by mapping the airfoil into a near-circular shape with a known normal velocity distribution. The flow around this shape is solved by means of a complex potential made of a vortex, a doublet and a number of quadruplets. The solution is then transformed back to the airfoil plane where it is added to the known upstream flow field. The method is general and is not limited to a particular airfoil geometry as in previous work. Results of numerous test cases indicate that the method is both accurate and numerically efficient over a wide range of angles of attack and shear rates. Comparison is also made with the limited experimental data available.
机译：在这种方法中，无粘性的流场被分解为两部分：一个具有恒定涡度的已知场，代表上游剪切力；一个未知的非旋转场，代表由机翼引起的扰动流。通过将机翼映射为具有已知法向速度分布的近似圆形来处理未知场。通过由涡旋，双峰和多个四倍体构成的复数势可解决围绕该形状的流动。然后将溶液转化回翼型平面，然后将其添加到已知的上游流场中。该方法是通用的，并且不限于如先前工作中的特定翼型几何形状。大量测试案例的结果表明，该方法在较大的攻角和剪切速率范围内既准确又在数值上有效。还与有限的实验数据进行了比较。

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