Nonlinear Evolution of Stationary Crossflow Vortices in Swept-Wing Boundary Layers
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摘要: 横流失稳是后掠翼边界层主要的失稳形式.实验和数值研究发现在后掠翼边界层转捩之前,有一段较长的非线性幅值饱和阶段,因此线性稳定性不能有效预测横流失稳转捩过程,所以研究横流涡的非线性演化过程就极为必要.以NLF(2)-0415翼型为研究模型,在来流Mach数为0.8、后掠角为45°、攻角为-4°的条件下,用扰动方程计算了定常横流涡非线性演化过程.结果显示非平行性起着更加不稳定的作用.当基本波的幅值到达0.1时,非线性作用开始明显.横流涡经历了非线性幅值饱和过程,涡的形状呈现半蘑菇状,涡的涡轴与边界层外缘无粘势流平行.饱和涡使得原有流场发生极大的扭曲,流向速度和展向剖面出现了拐点.Abstract: The crossflow instability was one of the main forms of instability in sweptwing boundary layers. Previous investigations indicated that the stationary crossflow vortex underwent a period of nonlinear saturation before the transition, so the linear stability theories couldn’t effectively predict the transition process caused by the crossflow instability and it was essential to study the nonlinear evolution of stationary crossflow vortices. A 45°-sweepback and -4°-attack-angle NLF(2)-0415 airfoil under the condition of Ma=0.8 was studied. The nonlinear evolution of stationary crossflow vortices was computed with disturbance equations. The results illustrate that the nonparallelism plays a more unstable role. The nonlinear interaction begins to be obvious when the amplitude of the 1st order wave reaches around 0.1. The crossflow vortex undergoes a procedure of amplitude saturation, and the vortex shape is like a half-mushroom structure. The vortex axis is parallel to the inviscid potential flow direction. These vortices distort the velocities, and make the streamwise and spanwise velocity profiles go through inflection points.
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