多段翼型的大粒径过冷水滴结冰特征及气动影响分析

doi:10.16183/j.cnki.jsjtu.2017.08.005

摘要/Abstract

摘要： 基于验证有效的SJTUICE(Shanghai Jiao Tong University Icing Simulation Code)数值方法，模拟了大粒径过冷水滴(SLD)条件下多段翼型冰形特征,并与常规粒径条件作对比，通过计算流体力学方法分析了多段翼型在SLD条件与常规粒径条件结冰对气动影响的差异性.结果表明：SLD条件下，缝翼处结出的角冰更大且位置更靠后，襟翼处结冰的影响尤为明显，向前生长出较大冰角，造成缝道处流场严重改变.攻角6°～22° 范围内，SLD结冰对气动性能的改变远大于常规粒径条件，其中400μm粒径水滴结冰后最大升力系数的下降达63.5%，失速攻角大幅提前8°.

关键词: , 大粒径过冷水滴；多段翼型；结冰特征；气动影响

Abstract: This paper uses SJTUICE (Shanghai Jiao Tong University Icing Simulation Code) method of prediction and develops method for the aerodynamic analysis on highlift configurations. After validating the supercooled large droplet (SLD), particle trajectory and icing prediction on multielement airfoils, this paper characterizes the SLD icing accretions and aerodynamic effects on highlift configurations and compares them with nonSLD conditions. The result indicates that the quantity of ice increases, and the upwind horn on the suctionside of the slat grows lager and extends downstream under SLD condition. It is remarkable to detect that the SLD condition induces the large increment of horn ice on leading edge of flap. The ice shape has a larger growth angle that is about to lead to the clogging of the gap. With the angle of attack ranging from 6° to 22°, the SLD condition has a larger degradation on the aerodynamic performance comparison with nonSLD condition. It leads to the decreasing of lift coefficient by 63.5% and causes stall to occur 8° earlier.

Key words: supercooled large droplet (SLD), highlift configurations, icing accretions, aerodynamic effect

中图分类号:

V 211

李冬1，张辰1，王福新1，刘洪1，杨坤2. 多段翼型的大粒径过冷水滴结冰特征及气动影响分析[J]. 上海交通大学学报（自然版）, 2017, 51(8): 921-931.

LI Dong1,ZHANG Chen1,WANG Fuxin1,LIU Hong1，YANG Kun2. An Investigation on the Characteristics of Supercooled Large
Droplet Icing Accretions and Aerodynamic Effects on
HighLift Configuration[J]. Journal of Shanghai Jiaotong University, 2017, 51(8): 921-931.

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