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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

    14Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration

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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

    22

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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

    26Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration

    P l S

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    Polar Sweep

    27Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration

    O tli

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    Introduction Numerical Methodology

    1st High Lift Prediction Workshop Results

    Polar Sweep

    Stowing and Un-Stowing

    Summary

    Outline

    28

    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

    29Advanced Aerodynamic Analysis of the NASA High-Lift Trap Wing with a Moving Flap Configuration

    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