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could you please If I change the shape of airfoil,how can I get the data about cl cd cm vs alpha?
thank you very much
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**Describe the bug**
Some unitary tests exhib top_level_collect errors due to plugin behavior and relative imports.
By letting an unused import in the unitary test file (un-commented) : from fastoad…
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Setting laminar/turbulent transition locations is possible through modifying XFOIL global variables directly, but is not very user friendly. Wrapping the procedure in a Julia function would make the …
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Hello,
I'm learning Aeolus basic functions and validate simple profiles with Xfoil, Javafoil and Nasa FoilSim website https://www.grc.nasa.gov/WWW/K-12/airplane/foil3.html :
An ellipse 20% thickness…
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Running `xfoil_comparison.py` causes error when trying to parse the inviscid pressure coefficient file:
`IndexError: index 2 is out of bounds for axis 1 with size 2`
Looks like the `invcp.txt` fil…
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_Originally posted by @j2l in https://github.com/AeolusAero/Aeolus-AeroSketchPad/discussions/1#discussioncomment-2460437_ :
Actually, I think of two features:
- One simple and essential: being ab…
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Hi,
**Describe the bug**
The aerodynamic twist is applied in the wrong direction according to right-hand rule (positive `twist` results in downwards rotation of airfoil). This is also inconsistent…
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Can you tell me the default Mach number? Can I modify it manually? thank you
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Put together example(s) that recreate all of Malachi's figures in his thesis. Have each example linked to the figure number in his thesis. These might make a good set of examples on how to use the pyt…
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Hi, is it possible to replace the CFD solver with alternatives like xfoil?
Of cos, it may not be as accurate but for some cases, it can be valid and gives fast speed up.
Thanks!