Aeroelasticity

A 2 degree-of-freedom implicit structural solver has been implemented in NSMB. The coupling with the flow solver has allowed to calculate the flutter boundary in the time domain of a typical wing section representing a 2-D section near the wing tip of a 3-D wing. The ability of NSMB in predicting non-linear flutter has been demonstrated [Darracq, 1999 conf]:

i) transonic dip,
ii) limit cycle oscillations. Furthermore the Hopf bifurcation has been calculated