CL constraint for the MACH tutorial wing #678
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AbhijithMoni
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Thanks for catching this bug. We should have set this line as: |
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@friedenhe Thank you for addressing the issue and taking the time to implement the fix. |
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Hi,
I have a question regarding the aerostructural tutorial (MACH tutorial wing) for
runScript_AeroStruct.py
. In the problem description, it is stated that the Lift coefficient (CL) is expected to be 0.5. However, in the tutorial, the CL constraint is defined as follows:As a result, the solver converges to a CL of 0.3, not 0.5 as described.
Could you please clarify whether this discrepancy is intentional for the tutorial case, or if it might be an error in the script?
Many thanks in advance.
Best regards,
Abhijith
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