摘要
基于三维可压 Favre 质量加权平均 N—S方程,采用 B—L湍流模型模拟了高超声速条件下,球头大攻角双锥再入体周围的流场特征。利用一种改进的时间、空间二阶精度的 NND 格式,再现了高超声速条件下再入体周围的复杂流动现象,初步考察了激波与边界层的相互干扰,分析、对比了层流流场和湍流流场的流动现象的差别。
The hypersonic flow field around the reentry body is investigated by solving the 3D compressible mass weight-averaged Navier-Stokes equations,in which he B-L turbulent model is also incorporated.Utilizing an extended time/spatial second order NND scheme,the complecate folw phenomena around the reentry body are reproduced.The interaction between shock layer and boundary layer is also investigated.Finally,the differences between laminar folw and turbulent flow are analyzed by comparing the calculating results without/with the B-L turbulent model.
出处
《弹箭与制导学报》
CSCD
北大核心
2002年第S2期169-172,176,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金项目(批准号:19902021)
