摘要
为探究雷诺数对直升机机身气动特性的影响,基于风洞试验结果,采用CFD方法开展深入分析,CFD计算结果与风洞试验数据吻合较好。研究结果表明:雷诺数的增大使流动粘性降低,机身流动分离减弱,阻力系数降低;雷诺数增大到6Reexp后达到自准区雷诺数,阻力系数不再有明显的降低。0°迎角下8Reexp状态与0.5Reexp状态相比,阻力系数减小12%;与Reexp状态相比阻力系数减小6%。该结果可对风洞试验缩比1:16模型与1:8模型的试验结果修正提供一定参考。同时,雷诺数增大不会改变全机的失速迎角,但可改善全机失速后的纵向静稳定性;主桨毂这类周围流场分离剧烈的部件对雷诺数变化不敏感,且雷诺数变化后主桨毂尾流场对平尾的气动干扰几乎没有影响。
The influence of Reynolds number on the aerodynamic characteristics of one helicopter fuselage and its mechanism were explored based on CFD method.The calculation results were in good agreement with the wind tunnel test data.The research results showed that with the increase of Reynolds number,the viscosity decreases,and the flow separation of the reducer fairing,tail hatch and tank decreases,and the drag coefficient decreased.And 6 Re exp was the self-collimating Reynolds number,and the drag coefficient no longer decreased.The increase of Reynolds number could not change stall angle of attack of the helicopter fuselage,but it could improve the longitudinal static stability.Because of the flow field severe separation,main rotor hub was insensitive to the change of Reynolds number,and its wake flow had little aerodynamic interference on horizontal tail.
作者
高畅
毛旭
GAO Chang;MAO Xu(China Helicopter Research and Development Institute,Jingdezhen 333001,China)
出处
《直升机技术》
2023年第4期6-13,19,共9页
Helicopter Technique
关键词
直升机
雷诺数
气动特性
风洞试验
CFD
high-lift helicopter
Reynolds number
aerodynamic characteristics
wind tunnel test
CFD
