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Advanced Aerodynamic Analysis of theNASA High-Lift Trap Wing with a MovingFlap ConfigurationDavid M. Holman
26th June 2012
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Introduction Numerical Methodology
1st High Lift Prediction Workshop Results
Polar Sweep
Stowing and Un-Stowing Summary
Outline
2
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XFlow is a CFD software specifically designed to simulate complex
systems involving highly transient flows and even the presence ofmoving parts
These two areas have traditionally proven to be difficult to treat withclassic FEM/FVM schemes
Introduction
3Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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Introduction
4Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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The collision operator in XFlow is based on a multiple relaxation time
scheme
Numerical methodology
6Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
MRT
SRT
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As opposed to standard MRT, the scattering operator is implemented
in central moment space.
Numerical methodology
7Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
MRT
Raw moments
Central moments
SRT
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The approach used for turbulence modeling is the WMLES
The Wall-Adapting Local Eddy viscosity model provides a consistentlocal eddy-viscosity and near wall behavior
Numerical methodology
8Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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Introduction Numerical Methodology
1st High Lift Prediction Workshop Results
Polar Sweep
Stowing and Un-Stowing
Summary
Outline
10
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Trap wing "Config 1" (slat 30, flap 25) Mach = 0.2
Reynolds = 4.3E+6 based on MAC
Mean aerodynamic chord = 1.0067 m
No brackets
AoA: -4, 1, 6, 13, 21, 28, 32, 34 and 37 degrees
1st High Lift Prediction Workshop Results
11Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
All the computations were run on a single workstation with two
processors Intel Xeon E5620 @ 2.4 GHz (8 cores) and 12GB of RAM
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1st High Lift Prediction Workshop Results
12Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Virtual wind tunnel configuration: ( 40 x 15 x 30 ) m
Far field velocity as initial boundary condition
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1st High Lift Prediction Workshop Results
13Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Spatial discretization based on adaptive wake refinement
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1st High Lift Prediction Workshop Results
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The resolution is adjusted to keep the maximum number of elements
within the memory constrains of a single workstation (12GB)
1st High Lift Prediction Workshop Results
15Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
The computation time is 36hoursper run using two processors(8 cores)
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1st High Lift Prediction Workshop Results
16Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Volume rendering of the vorticity module for AoA = 13
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1st High Lift Prediction Workshop Results
17Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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1st High Lift Prediction Workshop Results
18Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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1st High Lift Prediction Workshop Results
20Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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1st High Lift Prediction Workshop Results
21Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Volume rendering of the vorticity module for AoA = 37
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Introduction Numerical Methodology
1st High Lift Prediction Workshop Results
Polar Sweep
Stowing and Un-Stowing
Summary
Outline
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Sweep from the linear part of the polar to the stall region
Polar Sweep
23Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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Polar Sweep
24Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Sweep from the linear part of the polar to the stall region
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Polar Sweep
25Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
P l S
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Polar Sweep
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P l S
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Polar Sweep
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O tli
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Introduction Numerical Methodology
1st High Lift Prediction Workshop Results
Polar Sweep
Stowing and Un-Stowing
Summary
Outline
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St i d U St i
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The geometry has been separated into different components for the
analysis of the stowing and un-stowing transitions of the flap andthe slat
Stowing and Un-Stowing
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Stowing and Un Stowing
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Two different transformation laws have been analyzed
Stowing and Un-Stowing
30Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Stowing and Un Stowing
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Stowing and Un-Stowing
31Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Stowing and Un Stowing
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Stowing and Un-Stowing
32Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Volume rendering of the vorticity module
Stowing and Un Stowing
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Stowing and Un-Stowing
33Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
Summary
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XFlow has been proved a reliable tool for traditional and advanced
aerodynamic problems involving presence of moving parts
Results for the 1st HLPWF in good agreement with experimentaldata
Successful polar sweep simulation
Proof of concept simulation for the stowing and un-stowingmaneuvers shows interesting results
Summary
34Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration
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Advanced Aerodynamic Analysis of theNASA High-Lift Trap Wing with a MovingFlap ConfigurationDavid M. Holman
26th June 2012