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Engineering, Operations & Technology Boeing Research & Technology
Boeing Sonic Boom Prediction Workshop Results 2nd AIAA Sonic Boom Prediction Workshop - Sci Tech 2017 - Grapevine, Texas
Todd Magee David Lazzara Boeing Research & Technology Boeing Research & Technology todd.magee@boeing.com david.s.Lazzara@boeing.com
January 7-8, 2017
Boeing Research & Technology | Aeromechanics Technology
Outline • FUN3D Results
– Method/Approach – Convergence – Nearfield Results for Required Grids – Comparison of Inviscid Flux/Limiter Methods
• Cart3D Results – Summary of Cases – General Cart3D Setup – Space-Marching Setup – Nearfield Results for Required Geometries and Adapted Grids
• Conclusions • Questions
| 2
Boeing Research & Technology | Aeromechanics Technology
�FUN3D Results
Magee | 3
Boeing Research & Technology | Aeromechanics Technology
FUN3D Method / Approach
�FUN3D flow solver Version-12.9-0555546 • Euler Equations • Conducted a flux methods and limiters trade for the NASA 25D with FTN • HLLC inviscid flux method with Van Leer limiter for all required cases
– This method has worked well for our preferred OVERFLOW method, so we wanted to see how the FUN3D implementation did for the required cases
• Initialized flow by running all cases 1st order �Utilized top three refined grids for each required case • Mixed grid for Axisymmetric body (1.00, 1.28, and 1.60) • Tetrahedra grid for JAXA WB (0.70, 0.83, and 1.00) • Mixed grid for NASA 25D with FTN (0.64, 0.80, 1.00)
Dual Intel Haswell 64-bit 14-core processors • NASA 25D Axisymmetric Body – 420 cores • JAXA WB – 420 cores • NASA 25D with FTN – 840 cores
Magee | 4
Boeing Research & Technology | Aeromechanics Technology
FUN3D was Utilized for all Required Cases
Magee | 5
NASA 25D with FTN
JAXA WB
NASA 25D Axisymmetric Body Equivalent Area
Boeing Research & Technology | Aeromechanics Technology
JAXA W/B Convergence History
Magee | 6
Iteration
R_1
0 3000 6000 900010-16
10-14
10-12
10-10
10-8
10-6
10-4
HLLC, Van Leer Flux Limiter, 0.70 gridHLLC, Van Leer Flux Limiter, 0.83 gridHLLC, Van Leer Flux Limiter, 1.00 grid
Iteration
C_L
3000 6000 9000
0.076
0.078
0.08
0.082
0.084HLLC, Van Leer Flux Limiter, 0.70 gridHLLC, Van Leer Flux Limiter, 0.83 gridHLLC, Van Leer Flux Limiter, 1.00 grid
Iteration
C_M
_y
3000 6000 9000-0.07
-0.068
-0.066
-0.064
-0.062HLLC, Van Leer Flux Limiter, 0.70 gridHLLC, Van Leer Flux Limiter, 0.83 gridHLLC, Van Leer Flux Limiter, 1.00 grid
Iteration
C_D
3000 6000 90000.006
0.0065
0.007
0.0075
0.008
0.0085
0.009
0.0095
0.01HLLC, Van Leer Flux Limiter, 0.70 gridHLLC, Van Leer Flux Limiter, 0.83 gridHLLC, Van Leer Flux Limiter, 1.00 grid
Boeing Research & Technology | Aeromechanics Technology
Undertrack Nearfield Results for NASA 25D Axi-Body At Multiple H/L
Magee | 7
X (meter)
dP/P
40 60 80 100 120 140 160 180 200 220-0.010
-0.005
0.000
0.005
0.010
X (meter)
dP/P
120 140 160 180 200 220 240 260 280 300-0.010
-0.005
0.000
0.005
0.010
X (meter)dP
/P200 220 240 260 280 300 320 340 360 380
-0.010
-0.005
0.000
0.005
0.010
H/L = 3
H/L = 1
H/L = 5
Boeing Research & Technology | Aeromechanics Technology
Undertrack Nearfield Results for NASA 25D Axi-Body
Magee | 8 X (meters)
(P-P
inf)
/Pin
f
100 150 200 250 300-0.006
-0.004
-0.002
0
0.002
0.004
0.006HLLC, Van Leer Flux Limiter, mixed 1.00 gridHLLC, Van Leer Flux Limiter, mixed 1.28 gridHLLC, Van Leer Flux Limiter, mixed 1.60 grid
H/L = 3
Boeing Research & Technology | Aeromechanics Technology
Undertrack Nearfield Results for JAXA WB at Multiple H/L
Magee | 9
X (meters)
dP/P
120 140 160 180 200-0.0050
-0.0025
0.0000
0.0025
0.0050
X (meters)
dP/P
40 60 80 100-0.0100
-0.0075
-0.0050
-0.0025
0.0000
0.0025
0.0050
0.0075
0.0100
H/L = 2.55
H/L = 0.85
Boeing Research & Technology | Aeromechanics Technology
Undertrack Nearfield Results for JAXA WB
Magee | 10
X (meters)
(P-P
inf)
/Pin
f
120 140 160 180 200 220 240 260 280 300-0.005
-0.004
-0.003
-0.002
-0.001
0
0.001
0.002
0.003
0.004
0.005
HLLC, Van Leer Flux Limiter, 0.70 gridHLLC, Van Leer Flux Limiter, 0.83 gridHLLC, Van Leer Flux Limiter, 1.00 grid
H/L = 2.55
Boeing Research & Technology | Aeromechanics Technology
FUN3D Undertrack Nearfield Results for NASA 25D FTN
Magee | 11
X (meters)
dP/P
40 50 60 70 80 90-0.015
-0.010
-0.005
0.000
0.005
0.010
0.015
X (meters)
dP/P
120 140 160 180-0.015
-0.010
-0.005
0.000
0.005
0.010
0.015
X (meters)
dP/P
200 220 240 260-0.015
-0.010
-0.005
0.000
0.005
0.010
0.015
H/L=1
H/L=3
H/L=5
Boeing Research & Technology | Aeromechanics Technology
FUN3D Undertrack Nearfield Results for NASA 25D FTN
Magee | 12
X (meters)
(P-P
inf)
/Pin
f
120 130 140 150 160 170 180-0.007
-0.006
-0.005
-0.004
-0.003
-0.002
-0.001
0
0.001
0.002
0.003
0.004
0.005
0.006
0.007HLLC, Van Leer Flux Limiter, mixed 0.64 gridHLLC, Van Leer Flux Limiter, mixed 0.80 gridHLLC, Van Leer Flux Limiter, mixed 1.00 grid
H/L = 3
Boeing Research & Technology | Aeromechanics Technology
Comparison of Several Inviscid Flux/limiter Methods for NASA 25D with FTN
Magee | 13
Boeing Research & Technology | Aeromechanics Technology
X (meters)
(P-P
inf)
/Pin
f
120 130 140 150 160 170 180-0.008
-0.006
-0.004
-0.002
0
0.002
0.004
0.006
0.008Van Leer flux construction, hvanalbada flux limiterVan Leer flux construction, no flux limiterVan Leer flux construction, Van Leer flux limiterHLLC flux construction, Van Leer flux limiterVan Leer flux construction, vanalbada flux limiterLDFSS flux construction, vanalbada flux limiter
Comparison of Inviscid Flux/limiter Methods - NASA 25DFTN
Magee | 14
Pg.15
Pg.16
Pg.17
Boeing Research & Technology | Aeromechanics Technology
X (meters)
(P-P
inf)
/Pin
f
132 134 136 138 140 142 1440.001
0.002
0.003
0.004
0.005
0.006
0.007Van Leer flux construction, hvanalbada flux limiterVan Leer flux construction, no flux limiterVan Leer flux construction, Van Leer flux limiterHLLC flux construction, Van Leer flux limiterVan Leer flux construction, vanalbada flux limiterLDFSS flux construction, vanalbada flux limiter
Magee | 15
Comparison of Inviscid Flux/limiter Methods - NASA 25DFTN
Boeing Research & Technology | Aeromechanics Technology
Magee | 16
Comparison of Inviscid Flux/limiter Methods - NASA 25DFTN
X (meters)
(P-P
inf)
/Pin
f
152 152.5 153 153.5 154-0.004
-0.003
-0.002
-0.001
0
Van Leer flux construction, hvanalbada flux limiterVan Leer flux construction, no flux limiterVan Leer flux construction, Van Leer flux limiterHLLC flux construction, Van Leer flux limiterVan Leer flux construction, vanalbada flux limiterLDFSS flux construction, vanalbada flux limiter
Boeing Research & Technology | Aeromechanics Technology
Magee | 17
Comparison of Inviscid Flux/limiter Methods - NASA 25DFTN
X (meters)
(P-P
inf)
/Pin
f
156 158 160 162 164-0.005
-0.004
-0.003
-0.002
-0.001
0
0.001
0.002Van Leer flux construction, hvanalbada flux limiterVan Leer flux construction, no flux limiterVan Leer flux construction, Van Leer flux limiterHLLC flux construction, Van Leer flux limiterVan Leer flux construction, vanalbada flux limiterLDFSS flux construction, vanalbada flux limiter
Boeing Research & Technology | Aeromechanics Technology
�Cart3d Results
Lazzara | 18
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Summary of Cases
�Non-adapted and adapted grids used for each case ▪ Axisymmetric Equivalent Area case ▪ JAXA Wing Body case ▪ NASA 25D with flow-through nacelle case
�CART3D flow-solver
▪ Finite volume, inviscid Euler solver, Cartesian Euler grid, with minor vertical stretching ▪ Grid-aligned shock, along with a small radius cylinder around the model for extraction of
flow state variables along linear sensors ▪ Parallel execution on single compute node
▪ Non-adapted cases: 20 core, 128 GB RAM nodes ▪ Adapted cases: 20 core, 512 GB RAM nodes
�Space-marching solver
▪ High-order finite difference Euler solver ▪ Propagates flow state variables from an inner cylinder boundary to an outer cylinder ▪ High density structured grid ▪ Parallel execution on a single compute node: 20 core, 128 GB RAM
Lazzara | 19
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General Cart3D Setup Full Cylinder State Variable Extraction
▪ Full model geometry, cylinder H/L = 0.25, 2 deg spacing (Axisymmetric case used half-model)
▪ Cylinder centerline aligned with free-stream vector ▪ Cylinder length 2L—3L
Lazzara | 20
Radius, H
Length, L
Altitude
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General Cart3D Setup (Cont.) Model Rotated for Grid-Aligned Azimuth Directions
▪ Model rotated about the free-stream velocity vector for each azimuth direction ▪ Requested azimuth directions are grid-aligned ▪ Non-adapted grids utilize pre-specified density boxes ▪ Model is rotated in pitch for grid-aligned shocks (including offset for sonic glitch) ▪ Adapted grids pursued to lower error on pressure signature functional
Lazzara | 21
0 deg. Grid-Aligned 30 deg. Grid-Aligned 50 deg. Grid-Aligned
Grid-Misaligned Direction
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General Cart3D Setup (Cont.) Functional Convergence Monitored
▪ Functional convergence of all line sensors tracked ▪ Total functional convergence tracked for each adaptation cycle
▪ Same for non-adapted cases ▪ Adaptation functional weighting emphasized grid-aligned azimuth direction ▪ Adaptation cycles chosen until further error improvement not seen ▪ Smallest resolution is 2.4 cm for all cases
Lazzara | 22
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Space-Marching Setup
�Concentric Cylinder Output ▪ High accuracy signature propagation for all
azimuth directions to a “frozen” signature with smaller computational expense
▪ MPI parallelism
▪ Ideal atmospheric model captures ambient change for large H/L
▪ Enables smaller CFD domain
▪ Introduced in AIAA 2016-2037
▪ Full-cylinder propagation and half-cylinder propagation available (with symmetry BC) ▪ Initial data sets (JAXA and NASA 25D cases)
incorrectly used the symmetry BC for full-model cases
▪ Analyses rerun without a symmetry BC using full-cylinder propagation and submitted
Lazzara | 23
Free-stream H/L = 1
H/L = 3
H/L = 5
H/L = 10
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Axisymmetric Equivalent Area Case
Lazzara | 24
Non-Adapted Grid 22601287 cells
Adapted Grid #25 41394292 cells
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Axisymmetric Equivalent Area Case
Lazzara | 25
Non-Adapted Grid Adapted Grid #8
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Axisymmetric Equivalent Area Case
Lazzara | 26
H/L = 1 H/L = 3 H/L = 5
�Non-adapted and adapted signatures agree well
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JAXA Wing Body Case
Lazzara | 27
Non-Adapted Grid 28809383 cells
Adapted Grid #25 19536135 cells
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JAXA Wing Body Case
Lazzara | 28
Non-Adapted Grid Adapted Grid #25
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JAXA Wing Body Case: H/L = 0.85
Lazzara | 29 �Non-adapted and adapted signatures agree well
Boeing Research & Technology | Aeromechanics Technology
NASA 25D with Flow-Through Nacelle Case
Lazzara | 30
Non-Adapted Grid 19994779 cells
Adapted Grid #25 49107331 cells
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NASA 25D with Flow-Through Nacelle Case
Lazzara | 31
Non-Adapted Grid Adapted Grid #25
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NASA 25D with Flow-Through Nacelle Case: H/L = 1
Lazzara | 32 �Non-adapted and adapted signatures agree well
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Conclusions
�FUN3D Analysis • HLLC Inviscid flux method with Van Leer flux limiter provide nearfield
results with low dissipation – However some nearfield signature features are unphysical – Convergence stalled on some provided grids
• Results similar for all inviscid flux methods and limiters tried in the study – Van Leer flux construction with hvanalbada flux limiter yields the most
dissipative solution
�Cart3d Analysis • Non-adapted and adapted signatures agreed well • Full-cylinder propagation needed for full-models
– Setting a symmetry BC will yield incorrect signature shapes • Space-marching capability greatly reduces computational expense
– Full-cylinder propagation more efficient and accurate than conducting the same simulation in CFD alone
Lazzara | 33
Boeing Research & Technology | Aeromechanics Technology
�Questions?
Author, 7/10/2014, Filename.ppt | 34
Boeing Research & Technology | Aeromechanics Technology
Boeing Research & Technology | Aeromechanics Technology
FUN3D Cp Contours and Convergence for NASA 25D Axisymmetric Body
Author, 7/10/2014, Filename.ppt | 36
Iteration
R_1
0 2000 4000 600010-17
10-15
10-13
10-11
10-9
10-7
10-5
10-3
HLLC, Van Leer Flux Limiter, mixed 1.00 gridHLLC, Van Leer Flux Limiter, mixed 1.28 gridHLLC, Van Leer Flux Limiter, mixed 1.60 grid
Iteration
C_D
0 2000 4000 6000 8000 10000
0.001
0.0015
0.002
0.0025
0.003
HLLC, Van Leer Flux Limiter, mixed 1.00 gridHLLC, Van Leer Flux Limiter, mixed 1.28 gridHLLC, Van Leer Flux Limiter, mixed 1.60 grid
Boeing Research & Technology | Aeromechanics Technology
Author, 7/10/2014, Filename.ppt | 37
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FUN3D Cp Contours for NASA 25D with FTN
Magee | 38
Top
Bottom
Boeing Research & Technology | Aeromechanics Technology
Iteration
C_L
0 5000 100000.06
0.065
0.07
0.075HLLC, Van Leer Flux Limiter, mixed 0.64 gridHLLC, Van Leer Flux Limiter, mixed 0.70 gridHLLC, Van Leer Flux Limiter, mixed 0.83 grid
FUN3D Convergence Histories for NASA 25D with FTN
Magee | 39
Iteration
R_1
0 5000 10000
10-13
10-11
10-9
10-7
10-5
10-3
HLLC, Van Leer Flux Limiter, mixed 0.64 gridHLLC, Van Leer Flux Limiter, mixed 0.70 gridHLLC, Van Leer Flux Limiter, mixed 0.83 grid
Iteration
C_M
_y
0 5000 10000-0.054
-0.052
-0.05
-0.048
-0.046HLLC, Van Leer Flux Limiter, mixed 0.64 gridHLLC, Van Leer Flux Limiter, mixed 0.70 gridHLLC, Van Leer Flux Limiter, mixed 0.83 grid
Iteration
C_D
0 5000 100000.008
0.009
0.01
0.011
0.012HLLC, Van Leer Flux Limiter, mixed 0.64 gridHLLC, Van Leer Flux Limiter, mixed 0.70 gridHLLC, Van Leer Flux Limiter, mixed 0.83 grid
Boeing Research & Technology | Aeromechanics Technology
Lazzara | 40
JAXA Wing Body H/L = 0.85: Symmetry BC Incorrectly Applied
Boeing Research & Technology | Aeromechanics Technology
Lazzara | 41
NASA 25D H/L = 1: Symmetry BC Incorrectly Applied
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