基于合成双射流的翼型阵风载荷减缓  

Airfoil gust load alleviation based on dual synthetic jets

作　　者：王浩[1] 罗振兵[1] 邓雄[1] 周岩[1] 张鉴源 赵志杰 WANG Hao;LUO Zhenbing;DENG Xiong;ZHOU Yan;ZHANG Jianyuan;ZHAO Zhijie(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航空学报》2024年第16期63-74,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金联合基金项目(U2141252);国家自然科学基金创新群体(T2221002);湖南省高层次创新人才项目(22+TDRCJH-02-050);国防科技大学青年创新奖项目(青创+2019+07+03);国家科技重大专项(J2019-III-0010-0054)。

摘　　要：为研究基于合成双射流的阵风减缓策略,针对NACA0012翼型在其上表面阵列式布置合成双射流激励器,通过反向射流方式主动诱导流动分离,并详细研究分离涡的演化及动态涡脱落过程,为开展基于零质量射流的载荷控制提供了新的理念。结果表明,随着动量系数Cμ的增大,合成双射流对于阵风载荷控制能力逐渐提高且没有造成升力系数CL较大的脉动,当Cμ=0.033时,后缘分离区发展到翼型中部位置,CL,max响应幅值降低了47.9%。由于后缘处分离区较大,关闭射流激励器后分离涡在上翼面的卸载过程会对CL造成较大影响,在气流冲击分离涡的过程中,上下翼面压差迅速增大进而造成CL迅速减小;针对这一过程研究Cμ阶梯递减控制,设置Cμ区间式变化,相较于持续施加恒定Cμ的情况,这一控制方法在达到相同减缓幅值的情况下能耗更低,且翼型处于高载荷冲击的时间也更短。To study the gust alleviation strategy based on Dual Synthetic Jets(DSJ),we arrange the actuators in an array on the upper surface of the NACA0012 airfoil,actively induce the flow separation through reverse jets,and study the evolution of the separated vortex and the dynamic vortex shedding,providing a new insight for load control based on the zero-mass jet.The results show that with the increase of the momentum coefficient Cμ,the control ability of DSJ over the gust load is gradually improved without causing large fluctuation of the lift coefficient CL.At Cμ=0.033,the trailing edge separation zone develops to the middle position of the airfoil,and the response amplitudes of CL,max decrease by 47.9%.Because of the large separation zone at the trailing edge,the unloading process of the separated vortex on the upper wing surface after closing the jet actuator will have a significant impact on CL.In the process of airflow impacting the separated vortex,the pressure difference between the upper and lower wings rapidly increases,leading to rapid decrease of CL.Then,aiming at this process,we study the Cμstep-decreasing control,and set the Cμinterval change.Compared with the case of continuously applying constant Cμ,this control method requires less energy consumption in achieving the same slowing amplitude,and the airfoil also spends less time under high load impact.

关 键 词：阵风减缓 合成双射流 分离涡 反向射流 涡脱落 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]