usuaero / machline Goto Github PK
View Code? Open in Web Editor NEWA modern, subsonic-supersonic, unstructured, aerodynamic panel code. We do linear aerodynamics for the twenty-first century.
License: MIT License
A modern, subsonic-supersonic, unstructured, aerodynamic panel code. We do linear aerodynamics for the twenty-first century.
License: MIT License
Wanted to clarify that the off body control points must be specified outside of the mesh? If they were specified as points within the mesh , would the code raise an error? If not how would these control points be treated? Thank you
I am trying to solve the flow over an arbitrary aircraft. I am able to solve the flow at subsonic speeds using the default formulation. But when I increase the flow velocity to Mach 1.4, I get the resulting error:
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/ ____
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/ MachLine (c) 2023 USU Aerolab
/ / / v4.0
/ _________/___/_______________
( (__________________________
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\
Got input file: user_Inputs/f22_input.json
Reading and analyzing surface mesh
User has selected linear-doublet-constant-source panels.
Reading surface mesh in from file user_Inputs/sample.stl... Done.
Surface mesh has 4938 vertices and 9575 panels.
Mesh set to mirror about xz plane.
Locating adjacent panels...Done. Found 14512 edges.
Calculating vertex geometric parameters... Done.
Initializing based on flow properties
Initializing flow-dependent panel properties... !!! Calculation of mirrored local scaled coordinate transform failed. Quitting..
This would make you think there is an error with the symmetric body but when running it again at Mach 2, I get this:
/
/
/
/ ____
/ / /
/ MachLine (c) 2023 USU Aerolab
/ / / v4.0
/ _________/___/_______________
( (__________________________
\ \ \
\ \ \
\ \ \
\ \___\
\
Got input file: user_Inputs/f22_input.json
Reading and analyzing surface mesh
User has selected linear-doublet-constant-source panels.
Reading surface mesh in from file user_Inputs/sample.stl... Done.
Surface mesh has 4938 vertices and 9575 panels.
Mesh set to mirror about xz plane.
Locating adjacent panels...Done. Found 14512 edges.
Calculating vertex geometric parameters... Done.
Initializing based on flow properties
Initializing flow-dependent panel properties... Done. Found 1881 superinclined panels.
Characterizing edges...Done. Found 51 wake-shedding edges.
Determining where vertex clones are needed... Done.
Cloning vertices at wake-shedding edges...Done. Cloned 38 vertices. Mesh now has 4976 vertices.
Initializing wake with a Trefftz distance of 2.9809E+01...Done. Created 204 wake vertices and 101 wake panels distributed between 51 strips.
Setting up panel singularity distributions... Done.
Placing control points using a direct offset of 1.0000E-07... !!! The number of unknowns is not the same as the number of control points. Quitting...
I have provided by sample code and mesh.
I suggest adding the topics aerodynamics
, cfd
, computational-fluid-dynamics
in the About section.
Hi dear MachLine team!
I started work with your software and received the follow error for the first one example:
Got input file: dev/input_files/half_wing_input.json
Reading and analyzing surface mesh
User has selected linear-doublet-constant-source panels.
Reading surface mesh in from file dev/meshes/half_wing_right.vtk... Done.
Surface mesh has 685 vertices and 1336 panels.
Mesh set to mirror about xz plane.
Locating adjacent panels...Done. Found 2020 edges.
Calculating vertex geometric parameters... Done.
Initializing based on flow properties
Initializing flow-dependent panel properties... Done. Found 0 superinclined panels.
Characterizing edges...Done. Found 19 wake-shedding edges.
Determining where vertex clones are needed... Done.
Cloning vertices at wake-shedding edges...Done. Cloned 19 vertices. Mesh now has 704 vertices.
Initializing wake with a Trefftz distance of 7.9603E+01...Done. Created 76 wake vertices and 38 wake panels distributed between 19 strips.
Setting up panel singularity distributions... Done.
!!! 'morino' is not a valid formulation. Quitting...
I changed "formulation"
parameter in .json
from "morino"
to "dirichlet-morino"
. Code works, but is it correct substitution?
P.S. Also, could you provide me papers of Core Goates from Literature section, please? I don't have access to these papers, but want to read them so much. I would be happy to stay in touch with you!
Hi,
My input mesh is a .stl file with the unit of meter and the free steam velocity with m/s which should output Newton as the unit of forces. With the model of 16 meters 1:1 helicopter, the output value (Cx) is 0.1635 in the longitudinal direction. The output forces are significantly smaller than expected and did not change with different free stream velocities. Also, the Cp values also remain constant. I have tried a few sample models and the values are still constant with different free stream velocities. Please advise if I have done anything wrong. Thank you.
Hi again,
I wanted to know is there any further guidance on running the Panair vs Machline Python script? I understand you need to have Panair installed and the executable within the Machline directory but where specifically does it need to be placed? Are there any other requirements to run the script (python libraries etc..)? Also, does the Python script need to be edited to run the comparison script?
Thanks for the help
Hi,
In a report I read, someone stated they were able to provide a velocity field to Machline with velocities at given control points on a body to the program?
Is this possible in this iteration as I can't seem to find documentation on how to do so, if so how can I?
Thanks for the help
panair comparison code calls paraview_functions.py which contains import paraview.simple as pvs, how is this code meant to be run with respect to the paraview application
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