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Merge pull request #541 from suavecode/avl_vsp_geometry_bug_fixes
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AVL and VSP Bug Fixes
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@planes
planes committed Dec 10, 2021
2 parents 36a559b + f685c51 commit 4a42c06
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Showing 296 changed files with 17,225 additions and 16,907 deletions.
10 changes: 3 additions & 7 deletions regression/scripts/AVL/avl_files/base.avl
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Original file line number Diff line number Diff line change
Expand Up @@ -44,11 +44,7 @@ SECTION
#Xle Yle Zle Chord Ainc Nspanwise Sspace
17.5681 5.5598 -0.6873 3.88 0.0472
AFILE
B737c.dat
CONTROL
slat -1.0 -0.075 0. 0. 0. +1
CONTROL
flap 1.0 0.7 0. 0. 0. +1
B737b.dat

SECTION
#Xle Yle Zle Chord Ainc Nspanwise Sspace
Expand All @@ -64,9 +60,9 @@ aileron -1.0 0.84 0. 0. 0. -1

SECTION
#Xle Yle Zle Chord Ainc Nspanwise Sspace
23.2506 16.5251 0.3686 1.7072 0.02
23.2506 16.5251 0.3686 1.7072 0.0026
AFILE
B737c.dat
B737d.dat
CONTROL
slat -1.0 -0.075 0. 0. 0. +1
CONTROL
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78 changes: 48 additions & 30 deletions ...ession/scripts/AVL/avl_files/batch_01.run → ...sion/scripts/AVL/avl_files/batch_0001.run
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Original file line number Diff line number Diff line change
@@ -1,18 +1,21 @@


---------------------------------------------
Run case 1: case_01_01
Run case 1: case_0001_0001

alpha -> alpha = -2.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -43,18 +46,21 @@


---------------------------------------------
Run case 2: case_01_02
Run case 2: case_0001_0002

alpha -> alpha = 0.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -85,18 +91,21 @@


---------------------------------------------
Run case 3: case_01_03
Run case 3: case_0001_0003

alpha -> alpha = 2.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -127,18 +136,21 @@


---------------------------------------------
Run case 4: case_01_04
Run case 4: case_0001_0004

alpha -> alpha = 5.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -169,18 +181,21 @@


---------------------------------------------
Run case 5: case_01_05
Run case 5: case_0001_0005

alpha -> alpha = 7.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -211,18 +226,21 @@


---------------------------------------------
Run case 6: case_01_06
Run case 6: case_0001_0006

alpha -> alpha = 10.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down
78 changes: 48 additions & 30 deletions ...ession/scripts/AVL/avl_files/batch_02.run → ...sion/scripts/AVL/avl_files/batch_0002.run
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Original file line number Diff line number Diff line change
@@ -1,18 +1,21 @@


---------------------------------------------
Run case 1: case_02_01
Run case 1: case_0002_0001

alpha -> alpha = -2.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -43,18 +46,21 @@


---------------------------------------------
Run case 2: case_02_02
Run case 2: case_0002_0002

alpha -> alpha = 0.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -85,18 +91,21 @@


---------------------------------------------
Run case 3: case_02_03
Run case 3: case_0002_0003

alpha -> alpha = 2.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -127,18 +136,21 @@


---------------------------------------------
Run case 4: case_02_04
Run case 4: case_0002_0004

alpha -> alpha = 5.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -169,18 +181,21 @@


---------------------------------------------
Run case 5: case_02_05
Run case 5: case_0002_0005

alpha -> alpha = 7.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down Expand Up @@ -211,18 +226,21 @@


---------------------------------------------
Run case 6: case_02_06
Run case 6: case_0002_0006

alpha -> alpha = 10.0
beta -> beta = 0.0
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
pb/2V -> pb/2V = 0.0
qc/2V -> qc/2V = 0.0
rb/2V -> rb/2V = 0.00000
flap -> flap = 0.00000
aileron -> Cl roll mom = 0.00000
elevator -> Cm pitchmom = 0.00000

alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
pb/2V = 0.0
qc/2V = 0.0
rb/2V = 0.00000
CL = 0.00000
CDo = 0.0
Expand Down
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