Quasi-static loads analysis of a 5-bladed rotor in maneuver using CFD/CSD coupling
Quasi-static loads analysis of a 5-bladed rotor in maneuver using CFD/CSD coupling
dc.contributor.author | Hong, S. | |
dc.contributor.author | Jung, S. | |
dc.contributor.author | Kim, K. | |
dc.contributor.author | Park, S.H. | |
dc.contributor.author | Lee, D. | |
dc.contributor.author | Lee, J. | |
dc.date.accessioned | 2022-10-04T07:23:46Z | |
dc.date.available | 2022-10-04T07:23:46Z | |
dc.date.issued | 2019 | |
dc.description.abstract | The airloads and structural loads of Light Civil Helicopter (LCH) rotor in a pull-up maneuver are investigated using a coupled approach between the computational structural dynamics (CSD) and computational fluid dynamics (CFD) methods. The LCH rotor characterized by 5-bladed system with elastomeric bearing and inter-bladed damper is modeled in the structural dynamics analysis. The periodic rotor solution along with its converged CFD/CSD delta airloads for steady level flight (? = 0.287) is used to perform the transient maneuver analysis. The resulting vehicle attitude angles and velocity profiles are then prescribed for the quasi-static maneuver analysis of the rotor. The predicted section airloads, vortex trajectories, angle of attack (AOA)distributions, and structural moments at specified instants and spatial locations are compared between transient CSD-alone predictions and quasi-static CFD/CSD maneuver results. It is demonstrated that CFD/CSD coupled results indicate more pronounced dynamic stall peaks and stronger 5 /rev oscillations on structural moments than those by the CSD-alone approach. | |
dc.identifier.other | ERF2019 0141 | |
dc.identifier.uri | https://hdl.handle.net/20.500.11881/4154 | |
dc.language.iso | en | |
dc.title | Quasi-static loads analysis of a 5-bladed rotor in maneuver using CFD/CSD coupling |
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