钝锥动态转捩风洞试验  

Dynamic boundary layer transition wind tunnel test of blunt cone

作　　者：张石玉[1] 赵俊波[1] 付增良[1] 周平 周家检[1] 梁彬[1] ZHANG Shiyu;ZHAO Junbo;FU Zengliang;ZHOU Ping;ZHOU Jiajian;LIANG Bin(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2022年第6期61-66,共6页Journal of Experiments in Fluid Mechanics

摘　　要：钝锥飞行器俯仰振动时,非对称边界层转捩区前后移动相对于俯仰角运动的滞后将产生显著的非定常气动效应,导致飞行器俯仰动稳定性降低,严重时甚至会导致运动失稳。将基于气浮轴承的动态试验技术与转捩红外测量技术相结合,建立了钝锥动态转捩风洞试验技术。该技术采用气浮轴承提供俯仰运动自由且阻尼极低的支撑环境,采用红外热像仪实时测量飞行器表面整体转捩状态。开展了9°钝锥标模动态转捩试验,研究模型绕俯仰轴转动时边界层转捩区前后移动的非定常气动作用与飞行器运动的耦合效应。测量试验观察到了动态转捩试验迎角振荡现象,并发现了转捩区前后移动相对于迎角振荡的滞后现象,获得了转捩滞后时间。The time delay effects of the boundary layer transition movement on the surface compared to aircraft pitching oscillation should produce serious unstable aerodynamic moments,which probably decrease the aerodynamic stabilities in the pitch direction,even leading to unpredicted pitching divergence in the reentry flight of the blunt cone.A boundary layer dynamic transition test technology of the blunt cone in the hypersonic wind tunnel is improved,using a gas bearing as support of the test model in order to realize free rotation of the test model in the longitudinal direction with extremely low damping moment.In addition,an infrared thermographic system is used to observe and estimate the boundary layer transition distribution on the model,to study the dynamic coupling phenomenon and interaction between boundary layer transition and longitudinal rotation of the model.A series of tests are completed using the blunt cone model of which the half cone angle is 9 degree,to study dynamic coupling effects between boundary layer transition and longitudinal rotation.As a conclusion,an unsteady oscillation phenomenon of angle of attack was observed when dynamic boundary layer transition occurred,and at the same time,the delay phenomenon and delay time of boundary layer transition to angle of attack rotation were identified.

关 键 词：钝锥 动态 边界层转捩 风洞试验 耦合 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]