an overview of contributions for nose landing gear configuration … · 2016-05-14 · background...
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![Page 1: An Overview of Contributions for Nose Landing Gear Configuration … · 2016-05-14 · Background –Available Database Nose Gear Test Series (2007-2009) NASA Langley Basic Aerodynamic](https://reader034.vdocuments.site/reader034/viewer/2022042403/5f15b76ad4535e3bf328040a/html5/thumbnails/1.jpg)
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An Overview of Contributions for Nose Landing Gear
Configuration – BANC-III Workshop
by
Mehdi R. Khorrami
Computational AeroSciences Branch
NASA Langley Research Center, Hampton, Virginia
21st AIAA/CEAS Aeroacoustics Conference
22-26 June 2015, Dallas, Texas
https://ntrs.nasa.gov/search.jsp?R=20160006060 2020-07-20T15:24:52+00:00Z
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High-Fidelity, 25% Scale
Lower Fuselage Section
Correct Gear Cavity Geometry
16 Dynamic Pressure Transducers (1 Roving)
~123 Static Pressure Ports
Removable Components
o Hydraulic, Electrical Lines
o Steering Mechanism
o Light Cluster
o Can Seal Gear Cavity
o All Above Partially dressed model (simplified gear)
Background – Gulfstream Aircraft Nose Landing Gear Model
Baseline open configuration for
benchmarking aeroacoustic Simulations
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Background – Available DatabaseNose Gear Test Series (2007-2009)
NASA Langley Basic Aerodynamic Research Tunnel (BART)
Closed-wall tunnel (Open-Circuit)
28” x 40” x 10’ test section
Steady and unsteady pressures, PIV
Test M = 0.12, 0.145, 0.166
Univ. of Florida Acoustic Flow Facility (UFAFF)
Open tunnel within a 100 Hz anechoic room
29” x 44” x 72” test section
Acoustic measurements (phased Array, individual microphones)
Steady and unsteady pressures
Test M = 0.145, 0.166, 0.189
Track A
Track B
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Data Reporting for BANC-III
Not as stringent as previous workshop
Code to Code comparisons
Integrated forces (Cx and Cz)
Steady pressure distribution on select subcomponents
Cp’rms value from nine surface sensors (400Hz – 10 kHz integration)
Surface pressure spectra
Velocity profiles at select locations
Farfield noise at few microphone locations in flyover direction
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Five independent groups (teams) provided results
Seven distinct datasets (five new) used in comparison
Force coefficients in X and Z directions
Cp’ rms values for nine sensor locations
Surface pressure spectra at nine sensors
Farfield noise at five microphone locations in flyover direction
Comparison of line profiles not performed
Comparison Summary
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Contributions to PDCC-NLG
EntitySolver Attributes Solution Attributes
Name TypeNumerical Scheme
Turbulence Model
Grid element count
tSim. time*
Cores/physical time
EXA PowerFLOWLBM
Structured D3Q19 LBM
LBM-VLES/RNG k-+swirl
369.2M voxels
30M surfels
0.1604 s
0.024s/0.2s576/8 days
KHI CflowComp. N-S
Unstructured hybrid+AMR
2nd order2nd order
DDES/S-A
36.5M cells
635K surf. elem.
2.94 s
0.206s128/29 days
NASA LaRC(adapted)
FUN3DURANS
Unstructured mixed element
2nd order2nd order
MDDES/S-A
58M cells
1.0M surf. elem.
4.92 s
0.148s/0.30s
ONERA CEDREComp. N-S
Unstructured2nd order
Implicit 1st orderZDES/
k- SST70M cells
850K surf. elem.
1.0 s
0.06s/0.102s480/18 days
NASA ARC LAVAURANS
Structured/unstructured
2nd order2nd order
DDES/
S-A
NASA LaRC(Coarse**)
FUN3DURANS
Unstructured mixed element
2nd order2nd order
MDDES/
S-A
24M cells
1.1M surf. elem.4.92 s
0.148s/0.30s
NASA LaRC(104M)
FUN3DURANS
Unstructured mixed element
2nd order2nd order
MDDES/
S-A
104M cells
2.7M surf. elem.4.92 s
0.148s/0.30s
* Transient/sampling** Initial effort
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Integrated Forces (Coefficients)
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(coarse)
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RMS Pressure Levels at Sensor Locations
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Surface Pressure Spectra at Sensor Locations
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Surface Pressure Spectra at Sensor Locations
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Surface Pressure Spectra at Sensor Locations
![Page 12: An Overview of Contributions for Nose Landing Gear Configuration … · 2016-05-14 · Background –Available Database Nose Gear Test Series (2007-2009) NASA Langley Basic Aerodynamic](https://reader034.vdocuments.site/reader034/viewer/2022042403/5f15b76ad4535e3bf328040a/html5/thumbnails/12.jpg)
Farfield Noise Comparison
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Flow
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Flow
Farfield Noise Comparison
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Summary
Code-to-code comparison of force coefficients showed relatively
consistent trends and levels
Significant variation in computed Cp’rms values was observed
among flow solvers and relative to measured values
Some Cp’rms values seemed to be inconsistent with associated
spectra
Computations attempted to capture high-frequency behavior
Farfield noise comparison showed fair agreement
Computed farfield noise requires further scrutiny
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Backup Slides
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Farfield Noise Comparison
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Flow
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Flow
Farfield Noise Comparison
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Farfield Noise Comparison
1 2 3 4 5 6 7 8 9 10 11
Flow
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Contributions to PDCC-NLG
EntitySolver Attributes Solution Attributes
Name TypeNumerical Scheme
Turbulence Model
Grid element count
tSim. time*
Cores/physical time
EXA PowerFLOWLBM
Structured D3Q19 LBM
LBM-VLES/RNG k-+swirl
369.2M voxels
30M surfels0.024s/0.2s 576/8 days
KHI CflowComp. N-S
Unstructured hybrid+AMR
MUSCL 2nd orderMFGS 2nd order
DDES/S-A
36.5M cells
635K surf. elem.
2.94 s
0.206s 128/29 days
NASA LaRC(adapted)
FUN3DURANS
Unstructured mixed element
Roe/no limiterBDF2OPT
MDDES/S-A
58M cells
1.0M surf. elem.
4.92 s
0.148s/0.25s
ONERA CEDREComp. N-S
UnstructuredRoe 2nd order
Implicit 1st orderZDES/
k- SST70M cells
850K surf. elem.
1.0 s
1.806s/0.102s480/18 days
NASA ARC LAVARANS
Structured/unstructured
4th order CD2nd order BD
DDES/
S-A
NASA LaRC(Pointwise**)
FUN3DURANS
Unstructured mixed element
Roe/no limiterBDF2OPT
MDDES/
S-A
24M cells
1.1M surf. elem.
NASA LaRC(104M)
FUN3DURANS
Unstructured mixed element
Roe/no limiter
BDF2OPT
MDDES/
S-A
104M cells
2.7M surf. elem.
* Transient/sampling** Initial effort
![Page 20: An Overview of Contributions for Nose Landing Gear Configuration … · 2016-05-14 · Background –Available Database Nose Gear Test Series (2007-2009) NASA Langley Basic Aerodynamic](https://reader034.vdocuments.site/reader034/viewer/2022042403/5f15b76ad4535e3bf328040a/html5/thumbnails/20.jpg)
Line-cut 4 (door
wake)
Line-cut 3 (torque-arm
wake)
Line-cut 2 (wheels
wake)
Selected locations for
reporting near surface cell
size
Line-cut 1A (starboard
wheel’s side –2D TKE
extraction)
Line-cut 1B (starboard wheel’s
side – Vorticity and velocity
extraction)
Note: red dots indicate the starting point of the line-cuts
Line Cut Locations
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Blue spheres correspond to selected locations
for reporting near surface cell size
Red spheres and lines highlight location and
orientation of the line cuts
1B 1A 2
3
4
Line Cut Locations
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Extracted Flow Quantities
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Line-cut 2 (wheels wake)
θe = 86°
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