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About classical problems of airfoil drag

机译：关于翼型阻力的经典问题

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The drag of airfoils has long been determined from measurements in the wake behind the airfoil. The well-known formula of Squire and Young can be used to transfer the measured data to infinity downstream of the airfoil, where an exact relation to the drag exists. The Squire-Young formula is reviewed and an uncertainty in its derivation is discussed. A new formula of the same type is then derived, which also contains an uncertainty. This uncertainty can be reduced by experimental and numerical investigations of the wake displacement. Conversely, the displacement and the momentum of the wake must be investigated to reduce the uncertainty of the Squire-Young formula. In the second part of the paper, the determination of the drag directly by integration of the skin friction is investigated. Such a calculation is not difficult if the boundary-layer characteristics are computed numerically. An additional pressure drag must be regarded in this case. A new formula for the pressure drag is derived which shows that the uncertainty of the Squire-Young type formulas is contained in the evaluation of the pressure drag. This is another reason for further research on wake displacement.
机译：长期以来，机翼阻力是根据机翼后面尾流中的测量值确定的。众所周知的Squire和Young公式可用于将测量数据传输到机翼下游的无限远处，在那里与阻力存在精确关系。审查了Squire-Young公式，并讨论了其推导中的不确定性。然后推导相同类型的新公式，其中也包含不确定性。这种不确定性可以通过尾流位移的实验和数值研究来减少。相反，必须研究尾流的位移和动量以减少Squire-Young公式的不确定性。在本文的第二部分中，研究了直接通过皮肤摩擦积分确定阻力的方法。如果边界层特征是通过数值计算的，则这样的计算并不困难。在这种情况下，必须考虑额外的压力阻力。推导了压力阻力的新公式，该公式表明在压力阻力的评估中包含了Squire-Young型公式的不确定性。这是进一步研究尾流位移的另一个原因。

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