Modal Analysis-Aircraft wing



Naca 64-012A profile was used. Surface of wing was reconstructed using spline fitting to the airfoil section points. Chord is 1 meter, span is 5 meter and thickness is 0.01m.

One side of the wing is completely fixed and material properties are constant and isotropic.

Below is a figure of the mesh. The mesh refinement was kept simple.

Note: This is not a real case example and no effort has been made to make it a real case scenario. Instead the main effort here was put in order to implement a small tool in python that could take data points of airfoils and automatically create the surface CAD step files of the plane wings.

And now some videos: