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Incorrect Inviscid Airfoil Analysis #54
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Version 3.0.14 just pushed, which includes this fix c43e79a! Should be available via |
Also, a unit test has been added for this case: 749cab5 |
Great, thanks for the quick fix! I suspected as much that there was some issue with the trailing edge after visualising the pressure coefficient distribution, but I assumed it may be due to an issue in enforcement of the Kutta condition. Some techniques, such as the constant-strength doublet-source panel method, do suffer from similar "spikes" at the trailing edge, and blunt ones are sometimes pretty screwy! |
Bug Description
Running an inviscid analysis on a NACA 0012 airfoil at 0 degrees angle of attack produces non-zero lift coefficient.
Steps to Reproduce
CL: -0.17311351475463538
Expected Behavior
CL: 0
System Information
The text was updated successfully, but these errors were encountered: