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首页> 外文会议>2008 National Academic Symposium for Ph. D. Candidates and Tri-University Workshop on Aero-Structural Mechanics amp; Aerospace Engineering(NASPCTUWMAE2008)（2008年国际航天航空工程会议暨2008年博士生学术会议（力学）） >Modelling the Aerodynamic Flow Transition in Hypersonic Boundary Layer
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Modelling the Aerodynamic Flow Transition in Hypersonic Boundary Layer

机译：模拟高超音速边界层中的空气动力流动过渡

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摘要

A laminar-turbulence transition model is proposed in this study that takes into account of the effects of different instability modes associated with the variations in Mach numbers of compressible boundary layer flows. The model is based on k-ω-γ three-equation eddy-viscosity concept with k representing the fluctuating kinetic energy, ω the specific dissipation rate and the intermittency factor γ. The particular features of the model are that: 1) k includes the non-turbulent, as well as turbulent fluctuations; 2) a transport equation for the intermittency factor γ is proposed here with a source term set to trigger the transition onset; 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 thickness δ, which are often cost-ineffective with the modern CFD methods; 4) in the fully turbulent region, the model retreats to the well-known k-ω SST model. This model is validated with a number of available experiments on boundary layer transitions 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.
机译：在这项研究中提出了层流湍流模型，该模型考虑了与可压缩边界层流的马赫数变化相关的不同失稳模式的影响。该模型基于k-ω-γ三方程涡流粘度概念，其中k代表波动动能，ω代表比耗散率和间歇因子γ。该模型的特殊特征是：1）k包括非湍流以及湍流​​波动； 2）在此提出了一个针对间歇因子γ的输运方程，其中设置了一个源项以触发过渡开始； 3）通过引入一个新的垂直于墙的长度标尺，本模型仅使用局部变量，而避免使用积分参数，例如边界层厚度δ，这对于现代CFD方法通常是成本低廉的； 4）在完全湍流区域，该模型后退到著名的k-ωSST模型。通过许多可用的边界层过渡实验来验证该模型，包括通过平板的不可压缩流，超音速流和高超音速流，零入射角的直/扩口锥等。证明了该模型可以成功地应用于工程各种空气动力学流动过渡的计算。

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