NACA 2412型翼型冰积预测及气动性能分析

M. Ferdous, Md. H. E. Haider
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引用次数: 0

摘要

不利的气象条件往往会导致飞机机翼截面、发动机舱等部位结冰,导致升力系数损失和阻力系数增大,影响飞机的控制和稳定性。本文研究了非对称翼型在三种不同环境和云层条件下的飞行结冰问题。在相同雷诺数下,利用质量和能量守恒定律和Messinger冻结分数模型建立的数值模型对前缘冰厚进行预测。随后,采用计算流体动力学(CFD)技术研究了结冰翼型气动性能的退化,并考虑了二维翼型几何形状周围的流场。空气动力学研究表明,积云嵌入层状云有助于在翼型前缘形成混合冰,造成最坏结冰情况,在相同的环境条件下,升力系数降低到90%,阻力系数增加到800%。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Prediction of ice accretion and aerodynamic performance analysis of NACA 2412 aerofoil
Abstract Adverse meteorological conditions often contribute to the formation of ice on aircraft wing section, engine nacelle and other parts leading to the loss of lift coefficient and increase in drag coefficient affecting aircraft control and stability. This paper addresses the problem of in-flight icing on an asymmetric aerofoil under three different ambient and cloud conditions. The study involves prediction of the leading-edge ice thickness using a numerical model developed from the mass and energy conservation law and Messinger freezing fraction model at the same Reynolds number. Later on, degradation in the aerodynamic performance of the iced aerofoil was also investigated using the computational fluid dynamics (CFD) technique, taking the flow field around a 2D aerofoil geometry into account. The aerodynamic study indicates that cumulus clouds embedded with stratified clouds contribute to the formation of mixed ice on aerofoil leading edge and causes the worst icing scenario reducing the lift coefficient to 90% and increasing the drag coefficient to 800% for the same ambient conditions.
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