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Title: Modeling of Ice Accretion over Aircraft Wings Using a Compressible OpenFOAM Solver

Abstract

A method to simulate ice accretion on an aircraft wing using a three-dimensional compressible Navier-Stokes solver, a Eulerian droplet flow field model, a mesh morphing model, and a thermodynamic model, is presented in this paper. The above models are combined together into one solver and implemented in OpenFOAM. Two-way coupling is achieved between airflow field calculation and ice simulation. The density-based solver rhoEnergyFoam is used to calculate the airflow field. The roughness wall function is proposed to simulate the roughness effect caused by ice accretion. For droplet flow field calculation, the Eulerian model is applied and the permeable wall boundary condition is used on the wing to simulate the droplet impingement. The icing thermodynamic model is built based on the Messinger model. The mesh morphing model adjusts the wing’s shape every time step based on the amount of accreted ice so that the airflow field is updated during the simulation. The effect of the ice accretion on the airflow is studied by comparing the aerodynamic performance—with and without ice. The ice accretion on the ONERA M6 wing model under a specific condition has been simulated to validate the solver’s performance and investigate the effect of the accreted ice on themore » aerodynamic performance.« less

Authors:
ORCiD logo [1]; ORCiD logo [2]
  1. University of Illinois at Chicago, Department of Mechanical and Industrial Engineering, Chicago IL 60607, USA
  2. University of Illinois at Chicago, Department of Mechanical and Industrial Engineering, Chicago IL 60607, USA, Argonne National Laboratory, Computational Science Division and Leadership Computing Facility, Lemont, IL 60439, USA
Publication Date:
Sponsoring Org.:
USDOE
OSTI Identifier:
1524131
Grant/Contract Number:  
ANL 4J-30361-0030A
Resource Type:
Published Article
Journal Name:
International Journal of Aerospace Engineering
Additional Journal Information:
Journal Name: International Journal of Aerospace Engineering Journal Volume: 2019; Journal ID: ISSN 1687-5966
Publisher:
Hindawi Publishing Corporation
Country of Publication:
Country unknown/Code not available
Language:
English

Citation Formats

Li, Sibo, and Paoli, Roberto. Modeling of Ice Accretion over Aircraft Wings Using a Compressible OpenFOAM Solver. Country unknown/Code not available: N. p., 2019. Web. doi:10.1155/2019/4864927.
Li, Sibo, & Paoli, Roberto. Modeling of Ice Accretion over Aircraft Wings Using a Compressible OpenFOAM Solver. Country unknown/Code not available. doi:10.1155/2019/4864927.
Li, Sibo, and Paoli, Roberto. Mon . "Modeling of Ice Accretion over Aircraft Wings Using a Compressible OpenFOAM Solver". Country unknown/Code not available. doi:10.1155/2019/4864927.
@article{osti_1524131,
title = {Modeling of Ice Accretion over Aircraft Wings Using a Compressible OpenFOAM Solver},
author = {Li, Sibo and Paoli, Roberto},
abstractNote = {A method to simulate ice accretion on an aircraft wing using a three-dimensional compressible Navier-Stokes solver, a Eulerian droplet flow field model, a mesh morphing model, and a thermodynamic model, is presented in this paper. The above models are combined together into one solver and implemented in OpenFOAM. Two-way coupling is achieved between airflow field calculation and ice simulation. The density-based solver rhoEnergyFoam is used to calculate the airflow field. The roughness wall function is proposed to simulate the roughness effect caused by ice accretion. For droplet flow field calculation, the Eulerian model is applied and the permeable wall boundary condition is used on the wing to simulate the droplet impingement. The icing thermodynamic model is built based on the Messinger model. The mesh morphing model adjusts the wing’s shape every time step based on the amount of accreted ice so that the airflow field is updated during the simulation. The effect of the ice accretion on the airflow is studied by comparing the aerodynamic performance—with and without ice. The ice accretion on the ONERA M6 wing model under a specific condition has been simulated to validate the solver’s performance and investigate the effect of the accreted ice on the aerodynamic performance.},
doi = {10.1155/2019/4864927},
journal = {International Journal of Aerospace Engineering},
number = ,
volume = 2019,
place = {Country unknown/Code not available},
year = {2019},
month = {6}
}

Journal Article:
Free Publicly Available Full Text
Publisher's Version of Record
DOI: 10.1155/2019/4864927

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Works referenced in this record:

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