Skip to content
New issue

Have a question about this project? Sign up for a free GitHub account to open an issue and contact its maintainers and the community.

Sign up for GitHub

By clicking “Sign up for GitHub”, you agree to our terms of service and privacy statement. We’ll occasionally send you account related emails.

Already on GitHub? Sign in to your account

Jump to bottom

AVL and VSP Bug Fixes #541

Merged
merged 15 commits into from
Dec 10, 2021
Merged

AVL and VSP Bug Fixes #541

Show file tree
Hide file tree
Changes from all commits
Commits
Show all changes
15 commits
Select commit Hold shift + click to select a range
227fb5f
corrections in geometry tranlation
mclarke2 Nov 20, 2021
66334f3
Updating plotting functions and control surface discretization flag
mclarke2 Nov 22, 2021
89300ad
updates to code
mclarke2 Nov 25, 2021
e882048
updates to avl data structure code
mclarke2 Nov 29, 2021
95db9ca
New regression files for AVL
mclarke2 Nov 30, 2021
065498b
Update create_avl_datastructure.py
mclarke2 Nov 30, 2021
c1c0cdf
filename edits for optimization
mclarke2 Dec 2, 2021
058e71f
corrections to avl branch
mclarke2 Dec 5, 2021
cfa87cd
correction to fuselage location
mclarke2 Dec 9, 2021
072e33a
corrections to AVL analysis
mclarke2 Dec 9, 2021
dabf0c7
updating avl settings
mclarke2 Dec 9, 2021
381215e
updates for PR
mclarke2 Dec 9, 2021
79bec33
updating branch with new develop
mclarke2 Dec 9, 2021
4633fb9
Update ICE_Test.py
mclarke2 Dec 9, 2021
f685c51
Corrections for PR
mclarke2 Dec 9, 2021
File filter

Filter by extension

Filter by extension
Conversations
Failed to load comments.
Loading
Jump to
Jump to file
Failed to load files.
Loading
Diff view
Diff view
10 changes: 3 additions & 7 deletions regression/scripts/AVL/avl_files/base.avl
View file
Open in desktop
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
Expand Down
78 changes: 48 additions & 30 deletions ...ession/scripts/AVL/avl_files/batch_01.run → ...sion/scripts/AVL/avl_files/batch_0001.run
View file
Open in desktop
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
View file
Open in desktop
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
Loading