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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