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Hello, I am trying to extract a state-space model for a wing with a flap at the tip. The code that I am using is based on the FlyingWing class template. I have the attached the solver settings file. I am using a M=5, N=52 discretisation and the assembled aeroelastic system, in modal coordinates, is of the form: Aeroelastic system assembled: Is there any setting in particular that would allow the flap to be modelled in the state-space system? Am I missing something? Thank you for your help. |
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Hi Pierre, Do you mind trying this in the dev_linear branch and seeing if this is still the case? If it is, would you mind sending me a script to generate the input files? It is not the first time we encounter this and might need to have a more in-depth look. Thanks, |
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For reference to close this discussion: it was indeed a bug and detailed in #192 and will be fixed in the next SHARPy release |
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For reference to close this discussion: it was indeed a bug and detailed in #192 and will be fixed in the next SHARPy release