Development of a three-dimensional icing simulation code in the NSMB flow solver

被引：5
|
作者：
Pena, Dorian [1 ,2 ]
Hoarau, Yannick [1 ]
Laurendeau, Eric [2 ]
机构：
[1] Univ Strasbourg, Equipe MECAFLU, Lab Sci Ingn Informat & Imagerie ICUBE, 4 Rue Blaise Pascal, F-67400 Strasbourg, France
[2] Ecole Polytech, Dept Genie Mecan, CP 6079, Montreal, PQ H3C 3A7, Canada
来源：
INTERNATIONAL JOURNAL OF ENGINEERING SYSTEMS MODELLING AND SIMULATION | 2016年 / 8卷 / 02期
基金：
加拿大自然科学与工程研究理事会;
关键词：
aircraft icing; Eulerian droplet transport equations; icing effect;
D O I：
10.1504/IJESMS.2016.075544
中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
An icing model is developed in the Navier-Stokes multi-block (NSMB) compressible solver. The code implemented in this study is based on an Eulerian formulation for droplets tracking solved implicitly by means of CGSTAB or SIP methods, a modified iterative Messinger model using an improved water runback scheme for ice thickness calculation and three-dimensional mesh deformation to track the ice/air interface through time. The whole process is parallelised with MPI for efficient calculations. Validation is performed on several test cases including NACA23012 and NACA00012 airfoils and ONERA-M6 swept wing. Pressure coefficients around iced 23012 airfoil are compared with experimental data. Rime icing is computed on a DLR-F6 wing/body configuration. In all studied cases, the results are in good agreement with the literature.
引用
收藏
页码：86 / 98
页数：13
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