Use or disclosure of the information contained herein is subject to specific written CIRA approval 1

CIRA icing codes and findings for the IPW benchmarks

F. Capizzano, P. Catalano , A. Carozza, D. Cinquegrana, F. Petrosino

CIRA – Centro Italiano Ricerche Aerospazialie-mail: f.capizzano@cira.it

1st AIAA Ice Prediction WorkshopWorkshop in Conjunction with the AIAA AVIATION 2021 Forum

All Virtual/Remote Participation26-29 July 2021

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Motivations

CIRA solvers

Ice-accretion chain

Specific findings and conclusions

Future works

OUTLINE

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Challenge: the numerical prediction of in-flight ice accretion is becoming a valid mean to demonstrate the compliance with certification rules

Physics: ice accretion is a time-dependent multi-disciplinary field (aerodynamic, thermodynamic, multi-phase flow, geometry handling)

Expertise: CIRA has a solid background in icing, both numerically (MULTICE, ZEN-IMP3D, SIMBA-ICE, OpenFoam) and experimentally (IWT facility). Participation in EU-funded projects ICE-GENESIS (SLD) and MUSIC-HAIC (Ice-Cristals).

Goal: coupling different methodologies to exploit their respective benefits towards the fully automatic prediction of the ice accretion process

MOTIVATIONS

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Method Data manag. Turbulent Droplet Thermodynamic Surface deformation

SIMBA-ICEIB-RANS

3D Finite-VolumeFully Unstruct. k-w TNT Eulerian Messinger Multistep

Dynamic-IB

MultiIcePotential-BL

2D Finite Diff.Structured - Lagrangian Messinger Multistep

Lagrangian

ZEN-IMP3DRANS

3D Finite VolumeMulti-Block Structured k-w TNT Eulerian - Multistep

Lagrangian

OpenFoamRANS

3D Finite-VolumeOctree k-w SST Lagrangian - -

MESS3DSurface

Finite VolumeFully Unstruct. - - Messinger Multistep

Lagrangian

CIRA NUMERICAL CAPABILITIES

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Air and water phases

FV method, 2nd order skew-symmetric CDS scheme

Green-Gauss cell-center gradient reconstruction

Implicit 2nd order time-accurate integration

Standard k-ω TNT and Kalitzin k-g turbulence models

Wall modelling for medimum/high Reynolds number flows

Hybrid RANS-LES method: eXtra Large-Eddy Simulation

(X-LES) proposed by J.C. Kok.

( )TEwvu ρωρκρρρρρ ,,,,,,=Q( )Twvu αααα ,,,=Q

SIMBA FRAMEWORK

Mesh generation

CAD direct input (e.g. STL-format)

Can treat multi-body configurations

Unstructured data management

Anisotropic refinements

Cell tagging using a ray-tracing technique

Buffer Layers

Window refinement

Interface with the flow solver for adaptive refinements

based on the flow-field solution

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Software package for evaluating ice-accretion on 2D airfoils

Panel method for the air-phase or imported by a CFD external solver

Lagrangian approach for evaluating droplet trajectories

Ice-accretion is computed by using the classical Messinger model.

Different approaches are available: predictor, predictor-corrector or multi-step.

MULTI-ICE FRAMEWORK

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Aerodynamics by in-house ZEN code

Structured multi-block flow solver for EULER-RANS-

URANS equations

Finite-Volume, cell-centered

Jameson-like scheme

Dual-time stepping for time-accurate simulations

Several turbulence models

TNT κ-omega applied

Impingment by in-house IMP3D code

Eulerian method

Drag, gravity and buoyancy terms in momentum

equations

Pressure and viscous terms neglected for particle

phase

Finite-Volume, cell-centered

Same grid as aerodynamics

( )TEwvu ρωρκρρρρρ ,,,,,,=Q

( )Twvu αααα ,,,=Q

ZEN-IMP3D FRAMEWORK

Hybrid RANS-LES: Confluence of wake and bundary layerDrag-reduction devices

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• OpenFOAM is free and open source framework

• OpenFOAM includes solvers for any application, including particles (Eulerian or Lagrangian approach)

• Capability to customize solvers and applications

• 2D and 3D geometries

OPENFOAM FRAMEWORK

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I/O interface

MESS3D FRAMEWORK

ZEN flow IMP3D drop

SIMBA flow SIMBA dropMESS3D

Unstructured Advanced Messinger model for mixed phase accretion

Input converted in unstructured-data format for MESS3D (if needed)

Iterative Messinger model distributes runback-out flow based on surface skinfriction/Euler velocities

HTC computed internally in the MESS3D code

Grid vertices deformations by averaging neighbors freezing-cells’ thickness

Strucured data stream

Unstrucured data stream

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Aerodynamic flow field on clean geometry

Ice accretion modelling

Modified geometry

t=tfin

noyes

stop

Eulerian / Lagrangian approach

IB / Body fittedapproach

Aerodynamic flow field on iced geometry

Water impingement evaluation

Multilayer PDEs Mass, thermal balance - Messinger model

ICE ACCRETION CHAIN

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11

GLAZE-ICEMVD = 20 µmLWC = 0.55 g/m3

Tp = 265.37°KSpray time = 7 min.Nsteps= 10

M = 0.33Re = 5.10*106

α = 3.5°c = 0.5334 m

NACA0012 NASA- RUN401

air-phase

air-phase

water-phaseice-accr.

mesh adapt.

water-phase

SIMBA-ICE: VALIDATING MULTI-STEP ACCRETION

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Free-streamM = 0.23Re = 5.03*106

α = 6°T = 291.2 °KPstatic = 83025 Pa

y/b = 0.5 y/b = 0.9

Note: wing placed in WT with AOA applied and slip-BCs at side-walls

SIMBA-ICE: CASES 111 AND 112

NACA 64A008 HTAIL

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Free-streamM = 0.23Re = 5.03*106

α = 6°T = 291.2 °KPstatic = 83025 Pa

Note: wing placed in WT with AOA applied and slip-BCs at side-walls

CASES 111 AND 112

Case-111: MVD=21µm Case-112: MVD=92µm

NACA 64A008 HTAIL

No SLD modelling!

SIMBA OpenFoam

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Free-streamM = 0.23Re = 4.9*106

α = 4°T = 291.2 °KPstatic = 84850 Pa

Slat

air-phase water-phase water-phase

Note: far-field domain-boundarieswith free-stream AOA

CASES 121 AND 122

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CASES 121 AND 122

Slat Main FlapCase-121: MVD=21µm

Slat Main FlapCase-112: MVD=92µm

No SLD modelling!

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CASE-241 (rime)M = 0.35Re = 3.8*106

α = 2°MVD = 30 µmT = 250.15 °KPstatic = 92528 PaLWC = 0.42 g/m3

Spray time = 5 min.

SIMBA-ICE: CASE-241

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CASE-242 (glaze)M = 0.31Re = 3.4*106

α = 2°MVD = 30 µmT = 266.05 °KPstatic = 92941 PaLWC = 0.81 g/m3

Spray time = 5 min.Nsteps= 10

air-phase water-phase

air-phase

SIMBA-ICE: CASE-242

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18 in NACA 23012 - Test case n. 242 MultiIce (Panel/Lagrangian)

MULTI-ICE: CASE-242

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72 in NACA 23012 - Test case n. 252 MultiIce (Panel/Lagrangian)

MULTI-ICE: CASE-252

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CASE-361 (rime)M = 0.32Re = 7.2*106

α = 0°MVD = 34.7 µmT = 257 °KPstatic = 92321 PaLWC = 0.50 g/m3

Spray time = 20 min.

Note: wing placed into WT with slip-BCs at side-walls

SIMBA-ICE: CASE-361

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CASE-361 (rime)M = 0.32Re = 7.2*106

α = 0°MVD = 34.7 µmT = 257 °KPstatic = 92321 PaLWC = 0.50 g/m3

Spray time = 20 min.

SIMBA-ICE AND ZEN-IMP3D-MESS3D: CASE-361

One-shot ice-accretion

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In general, the finite-volume Eulerian solvers SIMBA-ICE and ZEN-IMP3Dproved superior to the Lagrangian Multi-Ice and OpenFoam solvers when appliedto compute water droplet impingement for the IPW benchmarks.

Roughness, convective heat transfer, runback, water film formation, etc. have keyroles for the “glaze-ice” accretion (e.g. the NACA23012 case-241).

On the whole, the developed multi-step FV methods could be good candidates forfuture developments towards complete 3D ice-accretion estimation.

The flexible treatment of Cartesian meshing around complex geometries, likethose encountered in icing, makes the IB-method particularly attractive.

FINDINGS AND CONCLUSIONS

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CIRA is developing a multi-step and multiphase approach for ice-accretion:

• Remeshing technique for the multi-block structured solver ZEN-IMP3D.

• Remeshing/refining technique for the IB-solver SIMBA.

In parallel, CIRA is developing an ice-accretion method based on a modifiedMessinger 3D model.

CIRA is implementing new/improved SLD models into the in-house Eulerian 2D and 3D solvers.

FUTURE WORKS

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Questions