Closer look at the flight dynamics of wings with non-elliptic lift distributions

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dc.contributor.authorAldana, Estela Bragado
dc.contributor.authorLone, Mohammad M.
dc.date.accessioned2020-03-30T15:38:29Z
dc.date.available2020-03-30T15:38:29Z
dc.date.issued2020-01-05
dc.description.abstractPrandtl’s alternative solution for wings with minimum induced drag opens another route for improving aircraft performance especially at the conceptual design phase. In this work, the lateral-directional characteristics of such wings are studied for a glider use case from a per-spective that focuses on pro verse yaw and handling qualities. The authors propose an aileron design methodology that ensures roll authority and proverse yaw characteristics. The resultsshow that these conditions cannot be satisfied by a conventional Elliptic configuration, whereaswings with non-elliptic distributions provide several solutions. Non-linear flight dynamic mod-els of the configurations that provided maximum proverse yaw were assessed in an engineering simulator and compared against the baseline Elliptic case. Proverse yaw was observed in thesimulation data and pilot feedback indicated improved handling qualities in the non-elliptic cases. However, the inherent directional instability combined with other lateral-directional coupling effects masked the observations from the pilot’s perspective.en_UK
dc.identifier.citationBragado Aldana E, Mendez A & Lone M (2020) Closer look at the flight dynamics of wings with non-elliptic lift distributions. In: 2020 AIAA SciTech Forum, 6-10 January 2020, Orlando, Floridaen_UK
dc.identifier.urihttps://doi.org/10.2514/6.2020-0284
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/15342
dc.language.isoenen_UK
dc.publisherAIAAen_UK
dc.rightsAttribution-NonCommercial 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/*
dc.subjectAtmospheric Flight Mechanicsen_UK
dc.titleCloser look at the flight dynamics of wings with non-elliptic lift distributionsen_UK
dc.typeArticleen_UK

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