Icing on three-dimensional lifting surfaces has been shown to produce highly complex flowfields. However, there is a lack of experimental and computational information in the public domain regarding three-dimensional aerodynamics for iced commercial aircraft wing geometries. Recent work completed at NASA Glenn Research Center’s Icing Research Tunnel has developed realistic ice shapes for the leading edge of a 65% scale Common Research Model (CRM65). These ice shapes were then converted into artificial ice shapes that were used in aerodynamic testing at the Wichita State University’s Walter H. Beech Wind Tunnel on an 8.9% scale CRM65. RANS simulations were computed for one large leading-edge ice shape to assess the ability to predict the aerodynamic performance parameters and to better understand the flow physics. In general, RANS reasonably captures the complex “swept stall” flow features, which are dominated by strong spanwise flow and separation line breaks. Despite the flow complexity, the simulations are able to generally predict the chordwise pressure distributions even at high angles of attack. While the coefficients of lift, drag, and moment are more accurately captured at lower angles of attack than higher angles of attack, the agreement with experimental data is quite reasonable given the complexity of the flow around this iced swept wing.

已经表明，在三维提升面上结冰会产生高度复杂的流场。然而，在公共领域中，缺乏关于用于商用飞机机翼几何形状的三维空气动力学的实验和计算信息。NASA Glenn研究中心的“结冰研究隧道”最近完成的工作已经为65％比例的通用研究模型（CRM65）的前沿开发了逼真的冰块形状。然后将这些冰块形状转换为人造冰块形状，并在威奇托州立大学的Walter H. Beech风洞中以8.9％的CRM65进行了空气动力学测试。计算了一种大型前沿冰形状的RANS模拟，以评估预测空气动力学性能参数并更好地了解流动物理学的能力。一般来说，RANS合理地捕获了复杂的“横扫失速”流动特征，这些特征主要是强劲的展向流动和分隔线中断。尽管流量很复杂，但是即使在高攻角下，模拟也能够大致预测弦向压力分布。尽管升力，阻力和力矩系数在较低的迎角下比在较高的迎角下能更准确地捕获，但鉴于绕过这架冰掠机翼的气流非常复杂，因此与实验数据的吻合是非常合理的。