基于V形沟槽的机翼蒙皮减阻特性仿真分析

王巍; 黄茹; 周艾; 冯贺

doi:10.3969/j.issn.2095-1248.2023.02.010

沈阳航空航天大学学报 ›› 2023, Vol. 40 ›› Issue (2) : 83 -89. DOI: 10.3969/j.issn.2095-1248.2023.02.010

民用航空与安全工程

基于V形沟槽的机翼蒙皮减阻特性仿真分析

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Simulation analysis of drag reduction characteristics for wing skin based on V-shaped groove

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摘要

为减少飞机飞行阻力、提高气动效率，基于微沟槽减阻理论，对机翼蒙皮进行微沟槽设计和减阻特性分析。应用计算流体力学（Computational Fluid Dynamics，CFD）方法，对不可压缩流下的纵、横向微沟槽进行模拟。选取k-ω SST湍流模型，通过分析V形沟槽边界层区域的流动特征，探究不同尺寸V形沟槽的减阻特性与减阻机理，对横向V形沟槽的数量与位置进行优化设计。仿真结果表明，随着沟槽尺寸和迎角减小，减阻率增大，纵向沟槽最大减阻率可达9.31%，横向沟槽减阻率最大可达7.35%，优化后的沟槽减阻率提高了1.39%。

Abstract

In order to reduce the aircraft flight resistance and improve its aerodynamic efficiency， based on the micro-groove drag reduction theory， the micro-groove design and drag reduction characteristics analysis of the wing skin were conducted. The incompressible flows of longitudinal and transverse micro-groove were simulated using computational fluid dynamics （CFD） methods. The k-ω SST model was selected，and the drag reduction characteristics and mechanism on different sizes of V-shaped groove were investigated. By investigating the flow characteristics in the boundary layer， the number and position of transverse V-shaped groove were optimized. The results show that the drag reduction rate is increased with the decrease of groove size and angle of attack. The maximum drag reduction rate of longitudinal and transverse grooves are 9.31% and 7.35% respectively，and this rate of the optimized transverse groove is increased by 1.39%.