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Abstract
The main objective of the thesis is to investigate the nonlinear geometric effects on the static and dynamic stability of helicopter hingeless rotor in hover. this nonlinearity mainly arises frrm the contribution of the flap and lead-lag bending to the elastic twist. the unsteady aerodynamic model was adapted to include the effect of both the pulsating free stream ans the returning spiral wake. differernt deficiency functions were used; quasi steady C(k) = 1, theodorsen C(k) and lowey C’ (k,m.h) both divergence and flutter phenomena were studied