高超声速边界层工程转捩模式研究  

Engineering transition models for hypersonic boundary layer

作　　者：许丁[1] 马晖扬[1] 

机构地区：[1]中国科学院研究生院物理学院,北京100049

出　　处：《中国科学院研究生院学报》2009年第1期43-49,共7页Journal of the Graduate School of the Chinese Academy of Sciences

摘　　要：在流动从层流过渡到湍流的转捩区域,传统的湍流模式由于没有考虑到脉动的间歇性,因此不能很好给出转捩区域流动的发展过程.考虑湍流脉动的间歇性,引入间歇因子,根据Hassan构造湍流转捩模式的思想来建立基于SST湍流模式的湍流工程转捩模式.应用该工程转捩模式,数值模拟了轴对称高超音速尖锥绕流,计算结果与实验符合良好,表明作者发展的工程转捩模式可以成功应用于高超声速飞行器工程转捩问题的计算.The traditional transition models do not consider the intermittency of the disturbances in the transition region from the laminar to turbulent boundary layer, therefore they can not predict the transition process very well. The present paper considers the intermittency and develops an engineering transition model based on SST turbulence model, by introducing an intermittency factor and following Hassan＇ s idea of constructing the transition model. This model is applied to the numerical simulation of the axisymmetirc hypersonic flow around a sharp cone. The numerical results are in good agreement with the experimental data. It is shown that this model developed by the authors may be applied successfully to the engineering computation of the transition for the hypersonic aircrafts.

关 键 词：工程转捩模式 湍流模式 间歇性 

分 类 号：O354.4[理学—流体力学]