Figure: Steady-state reference solution at

Moo = 0.96.

Figure: Dynamic linearity test on mode n°1 at

Moo = 0.96Figure: AGARD 445.6 wing 1st - 2nd generalized displacements blended step at Moo = 0.96.

Figure: Aerodynamic transfer function matrix

[ Ham(k) ] at

Moo = 0.96.Figure: Frequency ratio

Iw and flutter index

Iv as a function of freestream Mach number

Moo.