应用协同射流原理的旋翼翼型增升减阻试验研究  

Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept

作　　者：张顺磊 杨旭东[1] 宋笔锋[1] 王博[1] 李卓远 ZHANG Shunlei;YANG Xudong;SONG Bifeng;WANG Bo;LI Zhuoyuan(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2021年第4期44-51,67,共9页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(11672243);装备预研领域基金(61402060203)。

摘　　要：协同射流技术作为一种新型主动流动控制技术,是突破旋翼翼型高增升减阻设计的最有潜力的发展方向之一。以OA312旋翼翼型作为基准翼型,研制微型涵道风扇组为驱动的旋翼翼型CFJ风洞测力模型,开展基于前缘高负压零质量内循环协同射流原理的旋翼翼型高增升减阻低速风洞试验,研究吹气口大小、吸气口大小和上翼面下沉量等基础参数对增升减阻的影响规律,探讨CFJ旋翼翼型关键参数最佳取值。结果表明:与OA312基准翼型相比,小攻角状态时,CFJ旋翼翼型可显著降低阻力系数,甚至出现"负阻力"现象,实现了零升俯仰力矩基本不变;大攻角状态时,CFJ旋翼翼型可显著提升最大升力系数和失速迎角,其中,最大升力系数可提升约67.5%,失速迎角推迟了近14.8°。As the novel active flow control technology,Co-flow Jet concept(CFJ)is one of the most potential methods to achieve the high lift enhancement and drag reduction of rotor airfoil.Based on the OA312 rotor airfoil,the CFJ rotor airfoil dynamometric model driven by the micro ducted fan group is designed.The low-speed wind tunnel test of high lift enhancement and drag reduction of rotor airfoil using Co-flow Jet concept with zero mass and high negative pressure at the leading edge is conducted.The influence of basic parameters such as the injection size,suction size and suction surface translation on lift enhancement and drag reduction is studied.The optimal values of key parameters of CFJ rotor airfoil are given.Results show that compared with the OA312 baseline airfoil,the CFJ rotor airfoil can significantly reduce drag coefficients at low angle of attack,and even achieve"negative drag"while the zero-lift pitch moment is basically unchanged.The CFJ rotor airfoil can significantly increase the maximum lift coefficient and the stall angle of attack at high angle of attack.The maximum lift coefficient can be increased by about 67.5%,and the stall angle of attack is significantly delayed by nearly 14.8°.

关 键 词：协同射流 增升减阻 主动流动控制 旋翼翼型 低速风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]