协同射流在垂直尾翼流动控制中的应用研究  

Application Research of Flow Control Using Co-flow Jet on a Vertical Tail

作　　者：史子颉 许和勇[1] 郭润杰 刘智胜 姜承尚 董芳馨 SHI Zijie;XU Heyong;GUO Runjie;LIU Zhisheng;JIANG Chengshang;DONG Fangxin(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》2022年第1期28-41,共14页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(11972306);大学生创新创业训练计划项目(S202010699364)。

摘　　要：飞机垂直尾翼的气动特性直接关系到垂直尾翼尺寸和质量,通过流动控制方法提高垂直尾翼的升力可以进一步减小垂直尾翼尺寸,对减小结构质量具有实际意义。采用计算流体力学方法,对垂直尾翼的协同射流主动流动控制进行数值模拟;研究射流动量系数对连续协同射流的影响规律,以及射流动量系数、堵塞比、喷口数量等参数对离散协同射流的影响规律。结果表明:对于连续型协同射流,随着射流动量系数的增大,增升减阻和抑制分离的效果越显著;对于离散型协同射流,随着堵塞比的增加,增升效果逐渐下降,但功耗也同时下降;随着喷口数量的增多,增升效果先增大后减小,综合气动效率有所提升。The aerodynamic characteristics of the vertical tail of an aircraft are directly related to the size and weight of the vertical tail.Increasing the lift force of the vertical tail using flow control can further reduce the size of the vertical tail,which is of practical significance for reducing the weight of the structure.The computational fluid dynamics(CFD)method is used to perform the numerical simulation for the active flow control of vertical tail using the co-flow jet technique.The influence law of jet momentum coefficient on continuous co-flow jet and the influence law of jet momentum coefficient and the paramaters of jet momentum coefficient,blockage ratio,injection hole number on discrete co-flow jet are studied.The results show that for the continuous co-flow jet,with the increase of jet momentum coefficient,the effectiveness of lift enhancement,drag reduction and separation suppression becomes more significant.For the discrete co-flow jet,the effectiveness of lift enhancement gradually decreases with the increase of the blockage ratio,and the power consumption also decreases at the same time.With the increase of the discrete hole number,the lift enhancement effect first increases and then decreases,and the comprehensive aerodynamic efficiency considering energy consumption is improved.

关 键 词：垂直尾翼 协同射流 离散协同射流 射流动量系数 堵塞比 喷口数量 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]