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dc.contributor.author Botha, JDM
dc.contributor.author Dala, L
dc.contributor.author Schaber, S
dc.date.accessioned 2016-08-22T11:38:16Z
dc.date.available 2016-08-22T11:38:16Z
dc.date.issued 2015
dc.identifier.citation Botha, JDM, Dala, L and Schaber, S. 2015. Optimisation of a novel trailing edge concept for a high lift device. Advances in Aircraft and Spacecraft Science, Vol 2(3), pp 329-343 en_US
dc.identifier.uri http://scholar.ndsl.kr/schDetail.do?cn=JAKO201521159149123
dc.identifier.uri http://hdl.handle.net/10204/8743
dc.description Copyright: 2015: Techno Press. Due to copyright restrictions, the attached PDF file only contains the abstract of the full text item. For access to the full text item, please consult the publisher's website. The definitive version of the work is published in Advances in Aircraft and Spacecraft Science, Vol 2(3), pp 329-343 en_US
dc.description.abstract This study aimed to observe the effect of a novel concept (referred to as the flap extension) implemented on the leading edge of the flap of a three element high lift device. The high lift device, consisting of a flap, main element and slat is designed around an Airbus research profile for sufficient take off and landing performance of a large commercial aircraft. The concept is realised on the profile and numerically optimised to achieve an optimum geometry. Two different optimisation approaches based on Genetic Algorithm optimisations are used: a zero order approach which makes simplifying assumptions to achieve an optimised solution: as well as a direct approach which employs an optimisation in ANSYS DesignXplorer using RANS calculations. Both methods converge to different optimised solutions due to simplifying assumptions. The solution to the zero order optimisation showed a decreased stall angle and decreased maximum lift coefficient against angle of attack due to early stall onset at the flap. The DesignXplorer optimised solution matched that of the baseline solution very closely. The concept was seen to increase lift locally at the flap for both optimisation methods. en_US
dc.language.iso en en_US
dc.publisher Techno Press en_US
dc.relation.ispartofseries Worklist;15337
dc.subject Aerodynamic design en_US
dc.subject High lift en_US
dc.subject Single slotted flap en_US
dc.subject Optimization en_US
dc.subject Aeroacoustics en_US
dc.title Optimisation of a novel trailing edge concept for a high lift device en_US
dc.type Article en_US


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