Aerodynamic wind tunnel tests were conducted to study the effects of various ice accretions on the aerodynamic performance of a 36-inch chord, two-dimensional business jet airfoil. Eight different ice shape configurations were tested. Four were castings made from molds of ice shapes accreted in an icing wind tunnel. Two were made using computationally smoothed tracings of two of the ice shapes accreted in the icing tunnel. These smoothed profiles were then extended in the spanwise direction to form a two-dimensional ice shape. The final two configurations were formed by applying grit to the smoothed ice shapes. The ice shapes resulted in as much as 48% reduction in maximum lift coefficient from that of the clean airfoil. Large increases in drag and changes in pitching moment were also observed. The castings and their corresponding smoothed counterparts yielded similar results. Little change in performance was observed with the addition of grit to the smoothed ice shapes. Changes in the Reynolds number (from 3 x 10(exp 6) to 10.5 x 10(exp 6) and Mach number (from 0.12 to 0.28) did not significantly affect the iced-airfoil performance coefficients.
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机译：进行了空气动力学风洞测试，以研究各种积冰对36英寸弦，二维商务喷气机翼型的空气动力学性能的影响。测试了八种不同的冰形配置。四个是由结冰的风洞中积聚的冰形模具制成的铸件。使用计算出的结冰隧道中积聚的两种冰形状的平滑跟踪来制作两种。这些平滑的轮廓然后在翼展方向上延伸以形成二维冰形状。最后两个构型是通过将砂砾涂在光滑的冰块上而形成的。冰的形状使最大升力系数比干净的机翼降低了48％。还观察到阻力的大幅增加和俯仰力矩的变化。铸件及其相应的平滑配对件产生相似的结果。在光滑的冰块形状上添加砂砾后，性能几乎没有变化。雷诺数（从3 x 10（exp 6）到10.5 x 10（exp 6）和马赫数（从0.12到0.28）的变化不会显着影响冰翼性能系数。
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