面向SLD适航需求的大型客机翼型结冰安全性研究

发布时间：2018-04-15 01:37

本文选题：飞行安全 + 结冰适航审定　；参考：《上海交通大学》2013年硕士论文

【摘要】：大粒径过冷水滴（SLD）的粒径大于50μm，超出了适航条例25部附录C的范围，撞击在机翼表面后可形成溢流结冰。这些积冰可严重改变机翼气动外形、降低气动性能，并造成襟翼缝隙结冰或卡死，形成重大飞行安全隐患。本文以最新结冰适航条例的内容为导向，针对现有大型客机结冰安全性研究中结冰模拟和结冰气动性能分析的不足，发展出适用于二维多段翼型的SLD结冰模拟和溢流结冰气动分析的方法。本文利用确定的方法进行了模拟计算，计算所得MD-LB606b多段翼型各翼段的结冰与NASA实验结果一致。此外还采用雷诺应力模型（RSM）计算了NACA23012m溢流结冰的最大升力系数和失速迎角，，并用于分析溢流结冰引发的翼型流动分离。本文计算结果与实验数据符合较好，表明研究方法适用于大型客机二维翼型的结冰气动安全评估。在评估大型客机单段翼型SLD结冰安全时，由于溢流冰脊对不同翼型的气动影响程度差别较大，本文分别对机翼超临界翼型和平尾翼型上的溢流积冰进行了气动力计算和分析。超临界翼型在受到溢流冰脊影响时，提前发生气动分离，升力大幅下降；平尾翼型受溢流冰脊影响较小，在大攻角下流动分离区减小。在评估大型客机多段翼型SLD结冰安全时，模拟结果表明多段翼型各翼段积冰量大于常规小粒径结冰积冰量，襟翼前缘冰角高度明显增大。多段翼型结冰后气动性能下降，在三段翼型中缝翼受结冰影响最大。此外，由于增升装置的作用，多段翼型的气动损失小于单段翼型。本文研究内容对大型客机的设计和适航审定具有一定指导意义。
[Abstract]:The diameter of large diameter supercooled water droplet SLD is more than 50 渭 m, which is beyond the range of appendix C of part 25 of the airworthiness regulations, and the overflow ice can be formed after impingement on the surface of the wing.These ice deposits can seriously change the aerodynamic shape of the wing, reduce the aerodynamic performance, and cause the flap gap to freeze or jam, resulting in a serious flight safety hazard.Based on the content of the latest icing airworthiness regulations, this paper aims at the deficiency of ice simulation and aerodynamics performance analysis of existing large passenger aircraft icing safety research.A method of SLD icing simulation and aerodynamics analysis for two dimensional multistage airfoils is developed.In this paper, the simulated calculation is carried out by using the deterministic method, and the calculated results are in agreement with the experimental results of NASA for each wing segment of the MD-LB606b multi-section airfoil.In addition, the maximum lift coefficient and stall angle of attack of NACA23012m overflow ice are calculated by using the Reynolds stress model (RSM), and the flow separation of airfoil caused by overflow icing is analyzed.The calculated results are in good agreement with the experimental data, which indicates that the proposed method is suitable for evaluating the icing aerodynamic safety of airfoils of large passenger aircraft.In order to evaluate the icing safety of single airfoil SLD for large passenger aircraft, the aerodynamic calculation and analysis of overflow ice accumulation on wing supercritical airfoil and tail wing are carried out because of the great difference in aerodynamic effect of overflow ice ridge on different airfoils.When the supercritical airfoil is affected by the spillway ridge, the aerodynamic separation occurs ahead of time, and the lift greatly decreases, while the flat-tail type is less affected by the spillway ice ridge, and the flow separation area decreases at the large angle of attack.When evaluating the icing safety of multistage airfoil SLD, the simulation results show that the ice accumulation in each wing of multistage airfoil is larger than that of conventional small particle size, and the ice angle of flaps leading edge is obviously increased.The aerodynamic performance of multi-section airfoil is decreased after icing, and the slit wing is most affected by icing in three-stage airfoil.In addition, the aerodynamic loss of multi-section airfoil is smaller than that of single-section airfoil due to the effect of lifting device.The research content of this paper has certain guiding significance to the design and airworthiness examination of large airliner.
【学位授予单位】：上海交通大学
【学位级别】：硕士
【学位授予年份】：2013
【分类号】：V211.41;V328

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