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首页> 外文期刊>Journal of Aircraft >Effect of Intercycle Ice Accretions on Airfoil Performance
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Effect of Intercycle Ice Accretions on Airfoil Performance

机译：轮间冰积对翼型性能的影响

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摘要

Results are presented of an experimental study designed to characterize and evaluate the aerodynamic performance penalties of residual and intercycle ice accretions that result from the cyclic operation of a typical aircraft deicing system. Icing wind-tunnel tests were carried out on a 36-in. chord NACA 23012 airfoil section equipped with a pneumatic deicer for several different Federal Air Regulation 25 Appendix C cloud conditions. Results from the icing tests showed that the intercycle ice accretions were much more severe in terms of size and shape than the residual ice accretions. Molds of selected intercycle ice shapes were made and converted to castings that were attached to the leading edge of a 36-in. chord NACA 23012 airfoil model for aerodynamic testing. The aerodynamic testing revealed that the intercycle ice shapes caused a significant performance degradation. Maximum lift coefficients were typically reduced about 60% from 1.8 (clean) to 0.7 (iced) and stall angles were reduced from 17 deg (clean) to 9 deg (iced). Changes in the Reynolds number (from 2.0 x 10~6 to 10.5 x 10~6) and Mach number (from 0.10 to 0.28) did not significantly affect the iced-airfoil performance.
机译：给出了一项实验研究的结果，旨在表征和评估由典型飞机除冰系统的循环运行导致的残余和循环间积冰的空气动力性能损失。结冰风洞测试是在36英寸上进行的。装有气动除冰器的NACA 23012翼型部分，适用于几种不同的联邦航空法规25附录C的阴云条件。结冰试验的结果表明，轮滑间的积冰在尺寸和形状方面比残留的积冰严重得多。制成了具有选定周期的冰块形状的模具，并将其转换为附着在36英寸前缘的铸件。 NACA 23012翼型模型，用于空气动力学测试。空气动力学测试表明，循环间的冰形状导致性能显着下降。通常，最大升力系数从1.8（清洁）降至0.7（结冰）约60％，失速角从17度（清洁）降至9度（结冰）。雷诺数（从2.0 x 10〜6到10.5 x 10〜6）和马赫数（从0.10到0.28）的变化不会显着影响冰翼性能。

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