usuaero / machline Goto Github PK

A modern, subsonic-supersonic, unstructured, aerodynamic panel code. We do linear aerodynamics for the twenty-first century.

License: MIT License

Makefile 0.13% Fortran 61.16% Python 38.71%

aerodynamics cfd panel-method panel-methods supersonic supersonic-flow subsonic incompressible-flow inviscid-flow low-order-aerodynamics unstructured-meshes panel-code

machline's Introduction

MachLine

MachLine (Multi-order Approach to Calculating High-speed Linear aerodynamics) is a modern, unstructured, subsonic/supersonic flow solver currently being developed by the AeroLab. It is a linear panel method based on the Prandtl-Glauert equation. MachLine will implement many features not available in legacy compressible panel methods, such as unstructured meshes, iterative matrix solvers, automatic wake modelling, low-order singularity distributions, and more.

THIS SOFTWARE COMES WITH ABSOLUTELY NO WARRANTY, EXPRESSED OR IMPLIED.

MachLine is under active development and is not yet fully capable. We anticipate development to be completed sometime in the summer of 2024. As new features are added, the documentation will be updated accordingly. Please refer to the documentation for the full scope of features currently available in MachLine.

Documentation

Documentation can be found on the MachLine Wiki. There, you'll find instructions on how to compile and run MachLine, an overview of the theory and implementation, and references to relevant literature to help with gaining a deeper understanding of linear panel methods.

machline's People

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terragord7 corygoates conner-carlile smkinney979

machline's Issues

Pan_air comparison code

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

Machline vs Panair Comparison

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

Off Body Control Points

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

add topics

I suggest adding the topics aerodynamics, cfd, computational-fluid-dynamics in the About section.

!!! 'morino' is not a valid formulation.

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!

Constant forces and Cp with different free stream velocity

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.

MachLine Velocity Inputs

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

Can't Solve when Mach>1

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:

            /
           /
          /
         /          ____
        /          /   /
       /     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... !!! 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.

Sample.zip

usuaero / machline Goto Github PK

machline's Introduction

MachLine

Documentation

machline's People

Contributors

Stargazers

Watchers

Forkers

machline's Issues

Pan_air comparison code

Machline vs Panair Comparison

Off Body Control Points

add topics

!!! 'morino' is not a valid formulation.

Constant forces and Cp with different free stream velocity

MachLine Velocity Inputs

Can't Solve when Mach>1

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