RANS and LES simulation of airfoil ice accretion aerodynamics

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Abstract

RANS and LES modeling are applied to the geometrically complex problem of glaze ice accretion on fixed-wing and rotorcraft airfoils. The shortcomings of transport based RANS turbulence models for these systems is demonstrated using three experimental data sets. The roles of meshing topology, turbulence model choice, and 2D assumptions are quantified. Despite best practice implementation of RANS modeling, results show that these methods consistently under-predict stall onset and high-α lift. The reason for this poor performance is parametrically explored. It is shown that the smaller-scale (O[102 μm]) and larger scale (i.e., bluff "horns") geometric features of the ice shapes that give rise to a rich inertial 3D unsteady flow, at and aft of the leading edge, are primarily responsible, as these are largely inaccessible to RANS. Implicit LES results are presented that demonstrate improvement in predicted aerodynamic performance.

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Turbulence models
Airfoils
Ice
Aerodynamics
Fixed wings
Glazes
Unsteady flow
Topology

All Science Journal Classification (ASJC) codes

  • Biomedical Engineering

Cite this

@article{4f9f9a192a4641a9a1686c7b0ed1a7b2,
title = "RANS and LES simulation of airfoil ice accretion aerodynamics",
abstract = "RANS and LES modeling are applied to the geometrically complex problem of glaze ice accretion on fixed-wing and rotorcraft airfoils. The shortcomings of transport based RANS turbulence models for these systems is demonstrated using three experimental data sets. The roles of meshing topology, turbulence model choice, and 2D assumptions are quantified. Despite best practice implementation of RANS modeling, results show that these methods consistently under-predict stall onset and high-α lift. The reason for this poor performance is parametrically explored. It is shown that the smaller-scale (O[102 μm]) and larger scale (i.e., bluff {"}horns{"}) geometric features of the ice shapes that give rise to a rich inertial 3D unsteady flow, at and aft of the leading edge, are primarily responsible, as these are largely inaccessible to RANS. Implicit LES results are presented that demonstrate improvement in predicted aerodynamic performance.",
author = "Brown, {Christine M.} and Kunz, {Robert Francis} and Kinzel, {Michael P.} and Lindau, {Jules Washington V.} and Jose Palacios and Brentner, {Kenneth Steven}",
year = "2013",
month = "1",
day = "1",
language = "English (US)",
volume = "51",
journal = "BME = Bio medical engineering / henshu, Nihon ME Gakkai",
issn = "1347-443X",
publisher = "Japan Soc. of Med. Electronics and Biol. Engineering",
number = "SUPPL.",

}

TY - JOUR

T1 - RANS and LES simulation of airfoil ice accretion aerodynamics

AU - Brown, Christine M.

AU - Kunz, Robert Francis

AU - Kinzel, Michael P.

AU - Lindau, Jules Washington V.

AU - Palacios, Jose

AU - Brentner, Kenneth Steven

PY - 2013/1/1

Y1 - 2013/1/1

N2 - RANS and LES modeling are applied to the geometrically complex problem of glaze ice accretion on fixed-wing and rotorcraft airfoils. The shortcomings of transport based RANS turbulence models for these systems is demonstrated using three experimental data sets. The roles of meshing topology, turbulence model choice, and 2D assumptions are quantified. Despite best practice implementation of RANS modeling, results show that these methods consistently under-predict stall onset and high-α lift. The reason for this poor performance is parametrically explored. It is shown that the smaller-scale (O[102 μm]) and larger scale (i.e., bluff "horns") geometric features of the ice shapes that give rise to a rich inertial 3D unsteady flow, at and aft of the leading edge, are primarily responsible, as these are largely inaccessible to RANS. Implicit LES results are presented that demonstrate improvement in predicted aerodynamic performance.

AB - RANS and LES modeling are applied to the geometrically complex problem of glaze ice accretion on fixed-wing and rotorcraft airfoils. The shortcomings of transport based RANS turbulence models for these systems is demonstrated using three experimental data sets. The roles of meshing topology, turbulence model choice, and 2D assumptions are quantified. Despite best practice implementation of RANS modeling, results show that these methods consistently under-predict stall onset and high-α lift. The reason for this poor performance is parametrically explored. It is shown that the smaller-scale (O[102 μm]) and larger scale (i.e., bluff "horns") geometric features of the ice shapes that give rise to a rich inertial 3D unsteady flow, at and aft of the leading edge, are primarily responsible, as these are largely inaccessible to RANS. Implicit LES results are presented that demonstrate improvement in predicted aerodynamic performance.

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M3 - Conference article

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JO - BME = Bio medical engineering / henshu, Nihon ME Gakkai

JF - BME = Bio medical engineering / henshu, Nihon ME Gakkai

SN - 1347-443X

IS - SUPPL.

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