混合层强化混合的数值研究

受 Ｗａｎｇ ＆ Ｆｉｅｄｌｅｒ（１９９７）的实验的启发，采用高阶精度的差分格式，通过数值模拟的方法，研究了二维混合层及限于两平板间的二维混合层（二维受限混合层）入口处加振动对提高混合层混合效率的作用．计算结果表明：对二维混合层，振动的频率越低，在混合层中产生的大尺度涡结构的尺度越大，在频率很低时，涡具有相似性；对限于两平板间的二维混合层，在一定的振动频率下，混合层中产生的涡较大而且破碎得也较好，这将有利于混合．这一结论与 Ｗａｎｇ ＆ Ｆｉｅｄｌｅｒ（１９９７）的实验观测到的结果是一致的．     

带展向曲率的超音速混合层中扰动演化的研究

超音速混合层的流动不稳定性较之亚音速或不可压的混合层大大减弱，为了提高混合效率， 通过数值模拟的方法分别研究了展向曲率、展向速度、来流马赫数等因素对混合效率所 起的作用. 计算结果表明：在给定展向速度的情况下，带有展向曲率的三维混合层，曲率越 大三维扰动增长率越大，而且法向的卷起范围也越大. 当展向曲率不为零时，展向速度的增 大也能有效地增强混合能力. 由流场中的高频扰动波产生的涡，在向下游发展过程中会有破 碎、拉伸，低频扰动波没有发现这一现象. 对于有展向曲率和展向速度的混合层，提高来流 马赫数时，流场中最不稳定扰动的增长率仍很大. 因此，这是一种提高混合层混合效率的新 途径.     

Mechanism of transition in a hypersonic sharp cone boundary layer with zero angle of attack

Firstly, the steady laminar flow field of a hypersonic sharp cone boundary layer with zero angle of attack was computed.Then,two groups of finite amplitude T-S wave disturbances were introduced at the entrance of the computational field,and the spatial mode transition process was studied by direct numerical simulation (DNS) method. The mechanism of the transition process was analyzed.It was found that the change of the stability characteristics of the mean flow profile was the key issue.Furthermore,the characteristics of evolution for the disturbances of different modes in the hypersonic sharp cone boundary layer were discussed.     

湍流边界层外区大尺度相干结构的理论模型及与实验的比较

本文基于流动稳定性理论,提出了一种解释湍流边界层外区大尺度相干结构产生机理的理论模型.将计算所得流线、等涡线分布及利用相干结构理论模型计算湍流边界层中平均温度分布的结果与实验比较,结果是比较满意的.     

Numerical Investigation on Inviscid Instability of Streaky Structures in Incompressible Boundary Layer Flow

Numerical investigation is made on the effect of streaky structures in transition by inviscid linear disturbance equation with temporal mode. Several disturbances with different streamwise wave numbers were induced, and the evolutions with time step were received. It suggests that the exponential growth and periodic variation of the waves are in existence. As the streamwise wave number increases, the disturbance growth rate begins by increasing, reaches a maximum at around α=0.4 with a disturbance frequency of 0.2186 ＋ 0.001457i, and then decreases. Furthermore, the eigenfunctions of pressure disturbance are plotted.     

湍流边界层近壁区单个相干结构的模拟 *

提出了湍流边界层近壁区单个相干结构的理论模型 .用数值模拟的方法研究了它们的演化 ,结果发现在很多方面它们与实验观测到的特性相符 .     

NUMERICAL INVESTIGATION OF EVOLUTION OF DISTURBANCES IN SUPERSONIC SHARP CONE BOUNDARY LAYERS

The spatial evolution of 2-D disturbances in supersonic sharp cone boundary layers was investigated by direct numerical simulation (DNS) in high order compact difference scheme. The results suggested that, although the normal velocity in the sharp cone boundary layer was not small, the evolution of amplitude and phase for small amplitude disturbances would be well in accordance with the results obtained by the linear stability theory (LST) which supposes the flow was parallel. The evolution of some finite amplitude disturbances was also investigated, and the characteristic of the evolution was shown. Shocklets were also found when the amplitude of disturbances increased over some value.     

超音速后掠椭圆柱横流定常涡的不稳定特性及转捩预测

实验发现,一定条件下超声速后掠圆柱的前半圆上可能发生定常涡引起的转捩.为了模拟高空超音速飞行器后掠翼前缘,以无限展向长度后掠椭圆柱为模型,基于eN方法,根据积分的N值,分析了迎风轴长度、Reynolds(雷诺)数、后掠角和Mach(马赫)数等参数的变化对超音速后掠椭圆柱横流定常涡不稳定性的影响.研究结果表明,后掠椭圆柱的迎风轴长度增加,会使横流定常涡的不稳定性增强;Reynolds数增大,使横流定常涡模态的不稳定性增强;不稳定性的强度与Reynolds数的大小为近似线性关系;飞行高度增加,Mach数变大,使横流定常涡的不稳定性变弱;后掠角在一定范围内的变化对横流定常涡的不稳定性影响不大.这些结果有助于提高对高空超音速飞行器翼前缘转捩机理的认识,为横流转捩预测提供理论指导     

槽道湍流近壁区相干结构的数值模拟

从流动稳定性理论中的共振三波出发，采用类似湍流直接数值模拟中的最小单元概念，用伪谱方法，对槽道湍流近壁区的单个相干结构进行了数值模拟，得到了与实验基本一致的结果，同时也搞清楚了在谱方法中用Ｃｈｅｂｙｓｈｅｖ－τ方法和配置点法哪个更精确的问题。     

Mode decomposition of nonlinear eigenvalue problems and application in flow stability

Direct numerical simulations are carried out with different disturbance forms introduced into the inlet of a flat plate boundary layer with the Mach number 4.5. According to the biorthogonal eigenfunction system of the linearized Navier-Stokes equations and the adjoint equations, the decomposition of the direct numerical simulation results into the discrete normal mode is easily realized. The decomposition coefficients can be solved by doing the inner product between the numerical results and the eigenfunctions of the adjoint equations. For the quadratic polynomial eigenvalue problem, the inner product operator is given in a simple form, and it is extended to an Nth-degree polynomial eigenvalue problem. The examples illustrate that the simplified mode decomposition is available to analyze direct numerical simulation results.