“Think of an airplane as a great body with its end structures (wings, horizontal tail
surfaces, vertical tail surfaces) that could have the possibility to change their shape as
they had internal nerve endings and muscles ...”
Deformed grid of TE (true scale), cross-
section y = 4.2 m (piezo-wing model).
Loading case: V/V* = 0.225, αg = 0°, h = 0
m, M = 0.1763.
Cp distribution on the wing and at cross-
section y=4.2 m (piezo-wing model)
Loading case: V/V* = 0.225 (see Table
3.3), αg = 0°, h=0, M=0.1763
Fluid dynamic grid of the piezo-wing
(pag.2 of 2)
