EXPERIMENTAL INVESTIGATION OF AERODYNAMIC INTERACTION EFFECT OF ROTOR WAKE ON FUSELAGE OF HELICOPTER

摘要

The interaction effect of rotor wake on fuselage of helicopter was investigated with exper- imental method. The results from experiment have proved that for the drag of fuselage the effect of rotor airflow is closely in connection with both the flight speed and the collective pitch of blades, while for the thrust and pitch moment of fuselage the collective pitch angle of blades plays more im- portant role.