摘要
有效减小诱导阻力对于飞机降低油耗、提高航程具有重要意义。针对某飞机翼身组合体构型,采用CFD数值模拟方法分析融合式翼梢小翼对飞机气动力特性的影响,尤其是其减阻效应;并给出翼梢小翼附近的空间流场。结果表明:带翼梢小翼后翼尖涡强度减弱,飞机阻力系数明显下降;固定升力系数0.5时,弯矩增加3.2%,阻力系数减小4.2%。
Effectively decreasing induced drag is of important significance for the aircraft to reduce the fuel consumption and increase the flight range.Numerical simulation with CFD methods are carried out to obtain the aerodynamic characteristics,especially the drag reduction effect of the fuselage and wing configuration with the fusion winglet.The results show that tip vortex is decreased and drag coefficient is obviously reduced.The bending moment coefficient can be increased by 3.2%and drag coefficient can be decreased by 4.2% when specifying the lift coefficient to be 0.5.
作者
马玉敏
魏剑龙
Ma Yumin;Wei Jianlong(The General Configuration and Aerodynamics Design and Research Department,The First Aircraft Institute,Xi＇an 710089,China)
出处
《航空工程进展》
CSCD
2018年第2期245-251,共7页
Advances in Aeronautical Science and Engineering
关键词
翼梢小翼
气动特性
诱导阻力
减阻
弯矩系数
数值模拟
winglet
aerodynamic performance
induced drag
drag reduction
bending moment coefficient
numerical simulation
