Validation of a rotor dynamic wake distortion model for helicopter maneuvering flight in both hover and forward flight conditions is considered in this paper. The development of the augmented finite state inflow model/dynamic inflow model to account for the main rotor wake distortion effect, the dynamic wake distortion model and a reduced order model to account for the main rotor/tail rotor/empennage interactions during maneuvering flight is briefly described. Simulated response predictions are compared with flight test data of the Black Hawk helicopter in both hover and forward flight conditions. The impact of the unsteady aerodynamics effect, the fuselage blockage effect and the gyroscopic feathering moment effect on the value of wake curvature parameter needed for accurate off-axis response predictions in hover is investigated.
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