Development of an Intermittency Equation for the Modeling of the Supersonic/Hypersonic Boundary Layer Flow Transition
Development of an Intermittency Equation for the Modeling of the Supersonic/Hypersonic Boundary Layer Flow Transition
复制标题
DOI：
10.1007/s10494-011-9336-1
复制
发表时间：
2011-03
期刊：
影响因子：
--
通讯作者：
L. Wang;S. Fu
中科院分区：
文献类型：
--
作者：
L. Wang;S. Fu
本文建立了一个间歇性输运方程来模拟超声速和高超声速条件下的层流-湍流边界层转捩。该模型考虑了与马赫数变化相关的不同不稳定模式的影响。该模型方程基于粘性因子γ的概念，在求解过程中与著名的SSTk-ω涡粘性模型耦合。本模式的特点是：（1）脉动动能既包括非湍流脉动，也包括湍流脉动：（2）所提出的湍流度因子γ输运方程通过源项触发转捩起始;（3）通过引入新的垂直于墙的长度尺度，本模型仅采用局部变量，避免了积分参数的使用，如边界层厚度δ，这在现代CFD方法中通常是不经济的;（4）在充分湍流区，模式退回到SST模式。该模型与一些现有的实验验证边界层转捩，包括不可压缩，超声速和高超音速流通过平板，直/扩口锥在零冲角等，它表明，本模型可以成功地应用于各种气动流动转捩的工程计算具有合理的宽范围的马赫数。
An intermittency transport equation is developed in this study to model the laminar-turbulence boundary layer transition at supersonic and hypersonic conditions. The model takes into account the effects of different instability modes associated with the variations in Mach numbers. The model equation is based on the intermittency factorγconcept and couples with the well-known SSTk–ωeddy-viscosity model in the solution procedures. The particular features of the present model approach are that: (1) the fluctuating kinetic energykincludes the non-turbulent, as well as turbulent fluctuations; (2) the proposed transport equation for the intermittency factorγtriggers the transition onset through a source term; (3) through the introduction of a new length scale normal to wall, the present model employs the local variables only avoiding the use of the integral parameters, like the boundary layer thicknessδ, which are often cost-ineffective with the modern CFD methods; (4) in the fully turbulent region, the model retreats to SST model. This model is validated with a number of available experiments on boundary layer transition including the incompressible, supersonic and hypersonic flows past flat plates, straight/flared cones at zero incidences, etc. It is demonstrated that the present model can be successfully applied to the engineering calculations of a variety of aerodynamic flow transition with a reasonably wide range of Mach numbers.