期刊
AEROSPACE SCIENCE AND TECHNOLOGY
卷 6, 期 3, 页码 171-183出版社
EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/S1270-9638(02)01148-3
关键词
Spalart-Allmaras model; compressible supersonic flows
This paper presents an extension of Spalart-Allmaras model to compressible supersonic flows. The model is implemented in a three-dimensionnal structured multi domain code using a high resolution implicit upwind scheme. Details of the formulation as well as the treatment of viscous gradients near boundaries are given. The method is validated for two different configurations. Firstly a cruciform. missile simulation shows the ability of the method to capture accurately the interaction between the fuselage vortices and the winglets enabling the correct evaluation of the roll induced moment. Secondly an internal inlet flow computation including bleeds and struts demonstrates the usefulness and the accuracy of the method for multiple boundary layers supersonic complex configurations. (C) 2002 Editions scientifiques et medicales Elsevier SAS. All rights reserved.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据