A low-order method is presented for aerodynamic prediction of wings operating at near-stall and post-stall flight conditions. The method is intended for use in design, modeling, and simulation. In this method, the flow separation due to stall is modeled in a vortex-lattice framework as an effective reduction in the camber, or "decambering." For each section of the wing, a parabolic decambering flap, hinged at the separation location of the section, is calculated through iteration to ensure that the lift and moment coefficients of the section match with the values from the two-dimensional viscous input curves for the effective angle of attack of the section. As an improvement from earlier low-order methods, this method also predicts the separation pattern on the wing. Results from the method, presented for unswept wings having various airfoils, aspect ratios, taper ratios, and small, quasi-steady roll rates, are shown to agree well with experimental results in the literature, and computational solutions obtained as part of the current work.

中文翻译：

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预测未后掠翼分离和失速的低阶方法

提出了一种低阶方法，用于对在近失速和后失速飞行条件下运行的机翼进行空气动力学预测。该方法旨在用于设计、建模和仿真。在这种方法中，由于失速导致的流动分离在涡旋晶格框架中建模为弯度的有效减少或“去弯度”。对于机翼的每一部分，铰接在该部分分离位置的抛物线外倾襟翼通过迭代计算，以确保该部分的升力和力矩系数与二维粘性输入曲线的值匹配。截面的有效攻角。作为对早期低阶方法的改进，该方法还可以预测机翼上的分离模式。该方法的结果，