CIRA icing codes and findings for the IPW benchmarks
Transcript of CIRA icing codes and findings for the IPW benchmarks
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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: [email protected]
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