Recent Advances on Immersed Boundary Methods at …dutw1479.wbmt.tudelft.nl/~wim/euromech549/presentations/... · Recent Advances on Immersed Boundary Methods at the Italian Aerospace

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

Recent Advances on Immersed Boundary Methods

at the Italian Aerospace Research Center

Francesco Capizzano, Emiliano Iuliano

Centro Italiano Ricerche Aerospaziali

Fluid Mechanics

e-mail: [email protected]

e-mail: [email protected]

EUROMECH Colloquium 549

Immersed Boundary Methods:

Current Status and Future Research Directions

17-19 June 2013, Leiden, The Netherlands

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

Outline

� Motivations

� The simulation system

� High Reynolds number flows: wall-modelling

� eXtra Large Eddy (XLES)

� Water droplet impingement

� Work in progress


Motivations

� Easy geometry handling and fast mesh generation

for complex 2D/3D configurations of industrial

interest

� EU Projects:

o JTI-GRA: Joint Technology Initiative - Green Regional Aircraft

o JTI-GRC: Joint Technology Initiative - Green RotorCraft

o EXTICE: EXTreme ICing Environment


Mesh generation

� CAD direct input (e.g. STL file-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

Air-flow solver

� Finite Volume method, 2nd order CDS scheme

� Matrix artificial dissipation

� Green-Gauss cell-center gradient reconstruction

� Runge-Kutta pseudo-time integration

� Dual-time stepping for time-accurate integration

� k-ω TNT and k-g turbulence models

� Wall modelling for medimum/high Reynolds number flows

� eXtra Large-Eddy Simul. (X-LES) proposed by J.C. Kok.

( )TEwvu ρωρκρρρρρ ,,,,,,=Q

Simulation System


Two-Layer Wall Modelling

−=

=

∂

∂=

∂

∂+

∂

∂

+

−+

2

1

3,1)(

A

y

t

i

it

n

ey

ix

p

n

u

x

κµ

µ

µµwτ

+y

An iterative procedure is required to solve the equations simultaneously along with

the following B.C.:

� Flow state vector Q at the “F” point is obtained by a WLSQ interpolation from the nearest cell centers,

� No-slip wall at the surface.

(Capizzano, AIAA Journal Vol. 49, No. 11, November 2011)


( )

( )

( )

( )2

2

2

2

3

22

2

2

222

2222

2

22

)(3

22)(

)(

)()()(

3,1)(

∂

∂+−+

∂

∂+

∂

∂+

∂

∂=

∂

∂

−

∂

∂+

∂

∂+

∂

∂=

∂

∂

∂

∂+−

∂

∂++

∂

∂+

∂

∂=

∂

∂

=

∂

∂−

∂

∂+

∂

∂=

∂

∂

x

g

ggCx

ugC

x

g

xt

g

g

k

x

u

x

k

xt

k

x

T

x

k

x

uu

xt

E

ix

px

x

u

xt

u

tgi

gtg

ittk

ttki

ti

i

it

i

µσµβρρ

αµσµρ

ρµµσµ

ρ

κκµσµµµρ

µµρ

µ

µ

wτ

gk SS~

,~

An iterative procedure is required to solve the equations simultaneously along with

the following B.C.:

� Flow state vector Q at the “F” point is obtained by a WLSQ interpolation from the nearest cell centers,

� No-slip wall at the surface.

( ) ( )F

ii

F

x

p

x

pgkEuugkEuu

∂

∂=

∂

∂= ,,,,,,,,, 3131 ρρρρρρρρρρ

0,02

31 =∂

∂====

x

Tgkuu

…results at 21th AIAA-CFD next week.

Two-Layer Wall Modelling


Outline

� Motivations






(from Kok J.C., AIAA paper

2004-264, January 2004)


X-LES results

Benchmark Experiments and Computations for Airframe Noise

(BANC-I)

Reduced Landing Gear (RLG)

Vinf = 40 m/s,

Dwheel=0,4064 m

M = 0.12

Re = 1.0*106

Experiments:

Low speed wind tunnel of the

National Aerospace Laboratories

(NAL) in Bangalore, India


X-LES solution

M = 0.12, Re = 1.0*106

∆t Uinf /Dwheel = 6.94·10-3

CTU(t*Uinf/Dwheel) = 55

Mesh

• Dfar/d = 0.5

• Lref = 7

• Dwall/b = 4.11*10-3

• Ncell = 8,364,529

Averaged field: last 5 CTUs

X-LES results


X-LES solution

M = 0.12, Re = 1.0*106



Averaged field: last 5 CTUs

X-LES results


X-LES solution

M = 0.12, Re = 1.0*106



Mesh

• Dfar/d = 1.054

• Lref = 8

• Dwall/b = 4.11*10-3

• Ncell = 8,364,529

Statistics from 10CTUs to 55 CTUs

X-LES results


X-LES vs. URANS

X-LES solution

M = 0.12, Re = 1.0*106



URANS solution

M = 0.12, Re = 1.0*106




X-LES solution

M = 0.12, Re = 1.0*106



URANS solution

M = 0.12, Re = 1.0*106



X-LES vs. URANS


Outline

� Motivations







Water Droplet Impingement

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, 3DICE

codes) and experimentally (IWT facility). Coordinates the EU-funded

EXTICE project, devoted to Supercooled Large Droplets.

Goal: coupling two different methodologies to exploit their benefits towards the

fully automatic prediction of the ice accretion process

Eulerian approach for water droplet impingement – easy catch efficiency

computation

Immersed Boundary solution – easy geometry handling and mesh generation


Ice accretion simulation

Aerodynamic flow field on clean geometry

Ice accretion modelling

Modified geometry

t=tfin

no

yes

stop

Eulerian / Lagrangian

approach

Body fitted / IB

approach

Aerodynamic flow field on iced geometry

Water impingement evaluation

Convective heat transfer Mass, thermal balance - Messinger model


The Eulerian model describes the transport of a continuous particle medium (water

droplet) within a carrier gas flow (air).

Eulerian droplet model

Time variation Advection termGravity source

term

Aerodynamic (one-way)

interaction source term

Solved on the same mesh of the aerodynamic flow solver.

Catch efficiency (= dimensionless water mass flow on a solid surface) is automatically

derived from field variables.


NACA 64A008 horizontal tail

CASE

M = 0.23

Re = 5.03*106

α = 0°

MVD = 21 µµµµm

ρρρρ p /ρρρρgas = 816.3

10%

span

50%

span

75%

span


NACA 64A008 horizontal tail

CASE

M = 0.23

Re = 5.03*106

α = 6°

MVD = 21 µµµµm

ρρρρ p /ρρρρgas = 816.3

10%

span

50%

span

75%

span


Work in progress

Two-layer wall modelling based on simplified PDEs is started. First

results will be shown at next 21th AIAA-CFD.

Further X-LES accuracy studies are on going.

The Eulerian IB-solver for water droplets impingement prediction is

a good candidate for future developments towards complete ice-

accretion estimation.


�Capizzano F., “A Compressible Flow Simulation System Based on Cartesian Grids with Anisotropic

Refinements”, 45th AIAA ASME, Reno, Nevada, USA, 2007, AIAA Paper 2007-1450.

�Capizzano F., Catalano P., “RANS Simulations of Flows around Complex Geometries using Locally Refined

Cartesian Grids.”, ECCOMAS 2008, June 30 – July 5, 2008, Venice, Italy.

�Capizzano F., “Turbulent Wall Model for Immersed Boundary Methods”, AIAA Journal, Vol. 49, No. 11,

November 2011.

� Iuliano E. et al.,"Water Impingement Prediction on Multi-element Airfoils by means of Eulerian and

Lagrangian Approach with Viscous and Inviscid Air Flow ", AIAA 2006-1270 (2006).

� Iuliano E. et al.,"An Eulerian Approach to Three-dimensional Droplet Impingement Simulation in Icing

Environment", AIAA 2010-7677 (2010).

� Iuliano E. et al., “Eulerian Modeling of Large Droplet Physics Toward Realistic Aircraft Icing Simulation”,

Journal Of Aircraft Vol. 48, No. 5, September–October 2011.

�Capizzano F., Iuliano E., “An Eulerian Method for Water Droplet Impingement by Means of an Immersed

Boundary Technique”, Proceedings of the ASME 2012 Fluids Engineering Summer Meeting FEDSM2012,

July 8-12, 2012, Rio Grande, Puerto Rico.

References

Documents

Recent Advances on Immersed Boundary Methods at …dutw1479.wbmt.tudelft.nl/~wim/euromech549/presentations/... · Recent Advances on Immersed Boundary Methods at the Italian Aerospace