12 fares hilift
TRANSCRIPT
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Enrico Fabiano , Ehab Fares, Swen Nölting
Exa GmbH
Acknowledgements
Judith A. Hannon
Bruno Moschetta
Unsteady Flow Simulation
of High-Lift stall Hysteresis
using a Lattice Boltzmann
Approach
AIAA-2012-2922
30th Applied Aerodynamics
Conference
25-28 June, 2012, New Orleans, LA
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Overview
Introduction
–TrapWing Geometry
Numerical Method – Lattice-Boltzmann based code (PowerFLOW)
Turbulence Modeling
Boundary Conditions
Results – 1st High-Lift Workshop / AIAA 2011 - 0869 results review
– Simulation Overview
–Sensitivity to laminar regions
– Investigation of hysteresis effect Coarse and fine simulation
Conclusions & Outlook
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Introduction
Geometry and Measurements – provided through 1st High-Lift prediction
workshop held in June 2010
Model details: – Semi-span, three-element configuration
mounted on a body pod – Untwisted trapezoidal wing
– MAC of 39.6”, AR of 4.56, LE Sweep 29.97 °
– ReMAC =4.3e6 , Ma=0.2
Experimental details:
–NASA Langley 14’x 22’
– Forces, moments, Cp distributions
– Free and SA transition documented in Shown in NASA Ames tunnelMcGinley C.B., Jenkins L.N., Watson R.D., and Bertelrud A., “3-D High-Lift Flow-
Physics Experiment – Transition Measurements”, AIAA Paper, 2005-5148, 2005
Eliasson P., Hanifi A., Peng S.-H., “Influence of transition on high – lift prediction
for the NASA trap wing model”, AIAA Paper, 2011-3009, 2011
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Experiment - Uncorrected forces- increasing Alpha
Experiment - Uncorrected forces- decreasing Alpha
Trap Wing in the NASA Langley WT
Introduction
Hysteresis effect discussed
in the talk
Windtunnel Measurement ~30s per AoA
ΔAoA ~0.5°-2°
(~20s rotating, 8s data acquisition & 2s data writing)
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Overview
Introduction
–TrapWing Geometry
Numerical Method – Lattice-Boltzmann based code (PowerFLOW)
Turbulence Modeling
Boundary Conditions
Results – 1st High-Lift Workshop / AIAA 2011 - 0869 results review
– Simulation Overview
–Sensitivity to laminar regions
– Investigation of hysteresis effect Coarse and fine simulation
Conclusions & Outlook
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Lattice Boltzmann Method
Fluid properties are described by distribution functions
– f is the number density for particles with velocity value v at
( , , ) f x v t
( , ) x t
Discrete Lattice Boltzmann Equation (LBE)
– Advection is by a constant velocity
– BGK collision term
– Fluid variables are obtained via simple summations:
( , ) ( , ) ( , )i i i i f x v t t t f x t x t
bi i t x f t x ),(),(
( , ) ( , )bi i iu x t v f x t
Shan X., Yuan X.-F, and Chen H. “Kinetic theory
representation of hydrodynamics: a way beyond the Navier
Stokes equation”, J. Fluid Mech., Vol. 550, 2006, pp. 413-
441
Chen H., Orszag S., Staroselsky I., and Succi S., “Expanded
analogy between Boltzmann Kinetic Theory of Fluid and
Turbulence”, J. Fluid Mech., Vol 519, 2004, pp. 307-314
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Turbulence Modeling
LBM– VLES Turbulence modeling approach
– ‘Coherent’ statistically anisotropic eddies at larger scalescomputed
– Statistically universal eddies in the inertial & dissipation
ranges modeled Boltzmann-τ model, uses a modified relaxation parameter
Extended RNG 2-equation model
– Swirl term used to switch between modeling & simulating
eddies Extended wall model
– Rescale the thickness of the turbulent boundary layerto account for pressure gradient effects
Chen, H., Kandasamy, S., Orszag, S., Shock, R., Succi, S., and Yakhot, V., “Extended Boltzmann Kinetic Equation for Turbulent Flows,” Science, Vol. 301, 2003, pp. 633-636.
Chen H., Teixeira C., and Molving K., “Realization of Fluid Boundary Condition via Discrete Boltzmann Dynamics”, Int. J. Mod. Phys. C , vol.9, pp.1281-1292, 1998.
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Overview
Introduction
–TrapWing Geometry
Numerical Method – Lattice-Boltzmann based code (PowerFLOW)
Turbulence Modeling
Boundary Conditions
Results – 1st High-Lift Workshop / AIAA 2011 - 0869
– Simulation Overview
–Sensitivity to laminar regions
– Investigation of hysteresis effect Coarse and fine simulation
Conclusions & Outlook
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Results – Brackets influence
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Results – Brackets influence
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Model of TrapWing (with brackets) in the NASA Langley WT
Experimental lift polar
Results – Blockage effect
Unsteady Flow simulation of a High Lift Configuration using a
Lattice Boltzmann Approach AIAA 2011 – 0869
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AoA [°]
Uncorrected - increasing Alpha
Corrected - increasing Alpha
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Results - Blockage Effects - Lift
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Experiment - Uncorrected force
Experiment - Corrected forces
PowerFLOW - with WT wall
PowerFLOW - Free Air
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Experiment - Uncorrected forces
Experiemnt - Corrected forces
PowerFLOW - with WT wall
PowerFLOW - Free Air
Results - Blockage Effects - Drag
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C m y
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α []
Experiment - Uncorrected Moments
Experiemnt - Corrected Moments
PowerFLOW - with WT wall
PowerFLOW - Free Air
Results - Blockage Effects - Pitching Moment
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Simulation Overview – Meshes
Setup 1 Setup 2
Setup1 Setup 2
Finest voxel size 1.25mm 1.25mm
Total number of Voxels 127 million 79 million
CPU-Hours 16,000 12,000
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Results – Sensitivity to laminar regions
S t a b i l i t y a n a l y s i s
L a m i n a r R e g i o n s
L a m i n a r r e g
i o n s
f r o m E
x p e r i m e n t
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Results – Sensitivity to LR – Lift
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Results – Sensitivity to LR – AoA 36°
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Results – Sensitivity to LR – AoA 36°
LR from Experiment SA Laminar Regions
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Experiment - Uncorrected forces- increasing Alpha
Experiment - Uncorrected forces- decreasing Alpha
Model of TrapWing (with brackets) in the NASA Langley WT
Used in the present simulations
Results – hysteresis effect
Experimental lift polar.
Hysteresis effect
Rotation zone used to pitch the trapwing with an
LBM specific sliding mesh approachLattice Boltzmann approach for local reference frames
Commun. Comput. Phys Vol. 9, No. 5, May 2011
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Coarse case Fine case
Finest voxel size 1.875mm 1.25mm
Total number of Voxels 37 million 79 million
Total number of Surfels 5.4 million 9 million
Total number of Timesteps 1,454,700 3,313,660
Physical time 4.570s 5.280s
Covered AoA range 28° – 36° – 28° 32° – 36° – 32°
CPU-Hours 54,200 166,000
Results – hysteresis effect
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Coarse case
α=28°-36°-28° in 1° steps
Initialized from steady 28°
0.27s per 1°
(0.02s rotating, 0.15s settling & 0.1s sampling)
Results – hysteresis effect – Coarse case
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Results – hysteresis effect – Coarse case
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Results – hysteresis effect – Coarse case
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Results – hysteresis effect – Coarse case
Stall sequence - AoA 33°
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Results – hysteresis effect – Coarse case
Stall sequence - AoA 34°
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Results – hysteresis effect – Coarse case
Stall sequence - AoA 35°
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Results – hysteresis effect – Coarse case
Stall sequence - AoA 36°
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Results – hysteresis effect – Coarse case
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Results – hysteresis effect – Coarse case
AoA 33 Increasing AoA 33 Decreasing
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Results – hysteresis effect – Coarse case
AoA 34 Increasing AoA 34 Decreasing
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Fine case
α=32°-36°-32° in 1° steps
Initialized from steady 32°
Variable settling time
Results – hysteresis effect – Fine case
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Results – hysteresis effect – Fine case
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Results – hysteresis effect – Fine case
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Results – hysteresis effect – Fine case
l h ff
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Results – hysteresis effect – Fine case
AoA 32 Increasing AoA 32 Decreasing
l h ff
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Results – hysteresis effect – Fine case
AoA 33 Increasing AoA 33 Decreasing
l h i ff i
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Results – hysteresis effect – Fine case
AoA 34 Increasing AoA 34 Decreasing
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Results – hysteresis effect – Fine case
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Overview
Introduction
–TrapWing Geometry
Numerical Method – Lattice-Boltzmann based code (PowerFLOW)
Turbulence Modeling
Boundary Conditions
Results – 1st High-Lift Workshop / AIAA 2011 - 0869 results review
– Simulation Overview
–Sensitivity to laminar regions
– Investigation of hysteresis effect Coarse and fine simulation
Conclusions & Outlook
C l i & O tl k
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Conclusions & Outlook
Unsteady Flow Simulations
–Lattice Boltzmann Approach
– Trap Wing with brackets in the NASA Langley WT
Hysteresis Study – Sensitivity to laminar regions for HiLift flows
Stall behavior – Reasonable prediction of the hysteresis effect
Underlying physical phenomena correctly captured Hysteresis predicted ~1°AoA compared to Experiment
Future studies will address –
Larger settling time per AoA Better agreement with exp. pitch – pause approach
– Other transition data? – Dynamic laminar regions modification