Ice Accretion Modeling Using an Eulerian Approach for Droplet Impingement

Kim, Jee Woong; Garza, Dennis P; Sankar, Lakshmi N.; Kreeger, Richard E.

doi:10.2514/6.2013-246

Cited by 17 publications

(12 citation statements)

References 17 publications

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“…A minor deviation of results is obtained near to the stagnation point. The origin of this discrepancy is unclear but similar collection efficiency behavior with low droplet diameters using Eulerian droplet model was obtained by Kim et al on a two-dimensional MS-317 airfoil [6].…”

Section: B Onera M6 Swept Wingsupporting

confidence: 62%

“…In FENSAP-ICE, droplet equations are solved on computational grid by means of weak Galerkin finite element method and implicit time marching using GMRES [5]. Eulerian model for droplets tracking in finite volume formulation have been investigated in many studies [6,7,8,9], most of the approaches presented in these papers solve equations explicitly by means of Multi-Step Runge-Kutta integration.…”

Section: Introductionmentioning

confidence: 99%

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

Pena

Hoarau

Laurendeau

2016

IJESMS

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An icing model is developed in the NSMB (Navier-Stokes Multi-Block) 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 parallelized with MPI for complex multi-block configurations. The validated on several test cases including NACA23012 and NACA00012 airfoils and ONERA-M6 swept wing. Pressure coefficient around iced 23012 airfoil is 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.

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Section: B Onera M6 Swept Wingsupporting

confidence: 62%

Section: Introductionmentioning

confidence: 99%

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

Pena

Hoarau

Laurendeau

2016

IJESMS

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“…The cross sectional geometry of the ice accreted model ( 2D) is considered for the flow analysis using pressure-based conditions. Spalart-Allmaras (SA) 1-equation model (Spalart et al, 1992) is preferred for the flow analysis related to aerospace applications and it has shown good results for boundary layer flows under adverse pressure gradients (Kim et al, 2013). It is a well-known fact that the modification to the SA model (1-equation) has been developed primarily to address issues of under-resolved grids.…”

Section: Numerical Simulationmentioning

confidence: 99%

Experimental and computational study of ice accretion effects on aerodynamic performance

Prasad¹,

Rose

2020

AEAT

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Purpose The purpose of this paper is to analyse an actual representation of ice accretions, which are important during the certification process. Design/methodology/approach Ice accretion experiments are conducted in a low-speed subsonic wind tunnel testing facility to evaluate the influence of various ice shapes around the airfoil sections. Ice accumulation changes the shapes of local airfoil sections and thereby affects the aerodynamic performance characteristics of the considered NACA 23012 profile. The ice profiles are impregnated using balsa wood with glace, horn and mixed ice accretion cases for the detailed experimental investigation. Findings Computational fluid dynamics analysis is done to compute the influence of different ice shapes on the aerodynamic coefficients (Cl and Cd) while ice accretion occurs at the leading edge of the airfoil sections. It is observed that the Cl and Cd modified immediately more than 40% as compared to the clean wing configuration. In the same fashion, the skin friction coefficient also abruptly changes for different ice shapes that have the potential to induce flutter at the critical speed of the airplane. The computational solutions are further validated through wind tunnel experiments and recent literature concerning certification for flight in icing conditions. Social implications The ice accretion study on the aerodynamic surfaces can also be extended for wind turbine blades installed at different cold regions around the globe. Further, the propeller icing influences the entire rotorcraft aerodynamics at low temperature conditions and the findings of this study are strongly connected with such problems. Originality/value The aerodynamic characteristics of the baseline airfoil are greatly affected by the ice accretion problem. Although flight through icing condition endures for a short duration, the takeoff path and decision speed are determined based on airplane drag as per federal aviation regulations. Hence, the proposed study is focussed on a cost-effective approach to predict the effect of ice accretion to achieve optimum performance.

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“…In recent years, icing codes based on the solutions of the Reynolds-Averaged Navier-Stokes (RANS) equations have been developed such as LEWICE3D (NASA) (Bidwell and Potapczuk (1993)),FENSAP-ICE (McGill University) (Beaugendre et al (2006)), CANICE2D-NS (École Polytechnique Montréal) (Hasanzadeh et al (2013)), ONICE3D (ONERA) (Montreuil et al (2009)). Because of a seamless integration to Navier-Stokes solvers, an Eulerian formulation for droplet trajectories initially introduced by (Scott et al (1988)) have been implemented in several icing codes (Bourgault et al (1999); Jung and Myong (2013); Kim et al (2013); Montreuil et al (2009); Zhu et al (2012); Cao et al (2012); Jung et al (2011)). Benefits of an Eulerian approach are numerous, including the direct determination of the impingement efficiency without requiring a statistical averaging process, the computation of the droplet state vector in the entire domain without defining appropriate initial positions of the water droplets and the possibility to compute the droplet field on the same mesh used for the flow.…”

Section: Introductionmentioning

confidence: 99%

A single step ice accretion model using Level-Set method

Pena

Hoarau

Laurendeau

2016

Journal of Fluids and Structures

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A new approach using the Level-Set framework is developed in the NSMB (Navier-Stokes Multi-Block) compressible solver for modeling the ice/air interface evolution through time during in-flight icing. Droplet distribution and impingement efficiency are computed by an Eulerian approach and the accreted ice is calculated by a PDE model. An icing velocity field is introduced and the Level-Set equations are solved on body-fitted multi-block structured grids. The whole process is parallelized with the MPI library for efficient calculations. Single step icing is simulated on NACA23012 and NACA0012 airfoils and on the ONERA-M6 and the GLC-305 swept wings. In all the studied cases, the results are in good agreement with existing and available data validating the feasibility of the approach.

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Ice Accretion Modeling Using an Eulerian Approach for Droplet Impingement

Cited by 17 publications

References 17 publications

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

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

Experimental and computational study of ice accretion effects on aerodynamic performance

A single step ice accretion model using Level-Set method

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