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

页码：86 / 98

页数：13

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