The purpose of the research was to find if it is possible to have an unsymmetrical span load distribution on a monoplane wing at the stall without a rolling velocity. The investigation is based upon the Prandtl first order wing theory. It is shown that it is possible to have an unsymmetrical lift distribution at the stall if a certain shape is assumed for the curve of section lift coefficient vs. effective angle of attack. Two methods of determining such a solution for any particular wing shape are discussed. Curves are presented showing unsymmetrical solutions for a number of different wing shapes and also showing the resulting lift and rolling moment coefficients. The important conclusions are as follows:udud1. An unsymmetrical lift distribution across the span of a monoplane wing at the stall is possible.udud2. The unsymmetrical solution produces a rolling moment of the same order of magnitude as that caused by a fully deflected aileron.udud3. The unsymmetrical distribution can occur only in a very small range of angles of attack after the wing begins to stall.udud4. The magnitude of the maximum rolling moment coefficient and the difference between the angle of attack at which the maximum rolling moment occurs and the angle of attack for first stall are nearly the same for all of the wing shapes investigated.
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机译：该研究的目的是发现是否有可能在失速情况下在失速的单翼机翼上具有不对称的跨度载荷分布。该调查基于普朗特一阶机翼理论。结果表明，如果截面升力系数与有效攻角的关系曲线假定为某种形状，则失速时升力分布可能不对称。讨论了针对任何特定机翼形状确定这种解决方案的两种方法。曲线显示了许多不同机翼形状的不对称解，还显示了升力和侧倾力矩系数。重要结论如下： ud ud1。在失速情况下，跨单翼机翼跨度的升力分布可能不对称。 ud ud2。非对称解产生的滚动力矩与完全偏转的副翼所引起的滚动力矩相同数量级。在机翼开始失速之后，不对称分布只能出现在很小的迎角范围内。对于所有研究的机翼形状，最大侧倾力矩系数的大小以及发生最大侧倾力矩的迎角与首次失速的迎角之间的差值几乎相同。
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