| The goal of this research is to implement a state-of-the-art dynamic wake and inflow model within the UTIAS EH101 Cormorant Helicopter model with the intent to improve the incorrect initial off-axis response that occurs when the Pitt-Peters dynamic inflow model is used. A set of four first order ordinary equations, derived by Zhao, for the dynamic wake distortion states has been added to the augmented Pitt-Peters inflow module. Another goal of this research is to prove the effectiveness of the dynamic wake distortion effect on a different helicopter model other than the widely used UH-60 BlackHawk helicopter model by correlating the EH101 simulation results with the ones in literature. In hover, similar pitch and roll rate responses with the inclusion of the wake distortion effect have been observed. As airspeed increases however, the wake distortion effect for the EH101 model diminishes compared with the UH-60 model. |
