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.
Reference:
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
Botha, J., Dala, L., & Schaber, S. (2015). Optimisation of a novel trailing edge concept for a high lift device. http://hdl.handle.net/10204/8743
Botha, JDM, L Dala, and S Schaber "Optimisation of a novel trailing edge concept for a high lift device." (2015) http://hdl.handle.net/10204/8743
Botha J, Dala L, Schaber S. Optimisation of a novel trailing edge concept for a high lift device. 2015; http://hdl.handle.net/10204/8743.
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