【摘要】 在低湍流度风洞中针对NACA64A-204翼型后掠翼模型进行混合层流控制(HLFC)实验研究.通过萘升华流动显示技术以及热线测量边界层速度的方法,研究了不同吸气量条件下HLFC对后掠翼转捩位置以及流动稳定性的影响.实验结果表明:无吸气的情况下,转捩出现在x/c≈0.4,标准和两倍抽吸量条件下,转捩位置可以达到80%弦长位置(最小压力点下游).HLFC方法可以减弱后掠翼边界层平均流的扭曲,降低扰动之间的非线性作用,减小不稳定扰动波的能量,延迟转捩获得更大的层流区.更多还原

【Abstract】 Hybrid laminar flow control(HLFC) experiments were conducted in the low-turbulence wind tunnel on a NACA64A-204 swept airfoil.Naphthalene sublimation flow visualization technology and hot-wire measurement method were taken to examine the effects of suction quantities on transition location and hydrodynamic stability.Experimental results show that transition location occurs at x/c≈0.4 in the non-suction case,and transition location can reach 80% of chord length(behind the minimum pressure point) in both standard and twice suction quantities.The HLFC methods can reduce the distortion of the velocity profile,bring down the nonlinear interaction among the disturbances,decrease the energy of dominated perturbation,and delay transition to achieve lager laminar flow region.更多还原