Main static aeroelastic effects on sailplane longitudinal stability and control

In the paper the effects of the wing torsional deformation and of the fuselage bending deformation are considered, as being probabily the most important ones. The classical theoretical expressions for equilibrium and stability are therefore modified, in order to take into account these aeroelastic effects, and discussed. A comparison with experimental data registered in flight on a two-seater wooden sailplane allows an appreciation of the better approximation obtained.