基于升华法的后掠翼混合层流控制研究  

Investigation of HLFC on swept wing based on sublimation technique

作　　者：王菲[1] 额日其太[1] 王强[1] 郭辉[2] 苏沛然[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《实验流体力学》2010年第3期54-58,共5页Journal of Experiments in Fluid Mechanics

摘　　要：在低湍流度风洞中针对45°后掠角NACA64A-204翼型模型,采用升华流动显示技术研究不同吸气量和不同迎角状态下混合层流控制(HLFC)对转捩位置的影响。结合热线方法测量流向速度研究扰动增长的机制。实验结果表明:萘升华流动显示技术适合用来研究HLFC方法对后掠翼转捩的影响,可以直观和准确地表示后掠翼上的转捩位置;在无吸气的情况下,随着迎角从-6°到2°增大,层流区长度先增大后减小;HLFC方法可以显著推迟由横流不稳定触发的转捩;在同一迎角下增加吸气量,可以更有效地减小主要扰动波的能量。Sublimation flow visualization was used in the experiments conducted in the low-turbulence wind tunnel on a NACA64A-204 swept airfoil.The effect of the hybrid laminar flow control（HLFC） on the transition locations at different suction quantities and different attack angles was experimentally researched.Hot-wire measured streamwise velocity to study the disturbances growth mechanism.The results show that naphthalene sublimation flow visualization is appropriate for studying influence of the HLFC method on swept wing transition.The transition location could be displayed intuitively and accurately on swept wing.When there is no suction,the length of the laminar flow region will be increased first and then decreased with the increasing of the attack angle from-6° to 2°.The HLFC method can remarkably delay the transition caused by crossflow instability.The increase of the suction quantity can effectively reduce the energy of dominated disturbance wave at the same attack angle.

关 键 词：混合层流控制 流动稳定性 转捩 萘升华 横流 

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]