Aerodynamic design of advanced rear end for large passenger aircraft

Aerodynamic design of advanced rear end for large passenger aircraft

Salvatore Corcione, Vincenzo Cusati, Fabrizio Nicolosi

Abstract. This paper focuses on the aerodynamic design of an advanced rear end concept for a large passenger aircraft, such as the Airbus A320. The aim was to reduce the size of the horizontal tailplane to minimize the aerodynamic drawbacks related to longitudinal stability and control requirements. This reduction would lead to improved aircraft performance by reducing fuel burn and rear-end weight. Assuming the same position of the aerodynamic center of the horizontal tailplane of a conventional aircraft, the results of this investigation showed that the required stabilizing performance of the tail could be achieved with a smaller tail surface. A reduction of 6% in tail planform area was achieved by leveraging the unique aerodynamic characteristics of a forward-swept tail, combined with the implementation of a leading-edge extension device. The reduced wetted area and the lower weight of the horizontal empennage could result in fuel savings of 100 to 120 kg of fuel per 1,000 km. This is equivalent to approximately 1.0 to 1.2% for the specific aircraft category being considered.

Keywords
Aircraft Design, Forward Swept Tailplane, Leading Edge eXtension, Aerodynamics

Published online 11/1/2023, 5 pages
Copyright © 2023 by the author(s)
Published under license by Materials Research Forum LLC., Millersville PA, USA

Citation: Salvatore Corcione, Vincenzo Cusati, Fabrizio Nicolosi, Aerodynamic design of advanced rear end for large passenger aircraft, Materials Research Proceedings, Vol. 37, pp 435-439, 2023

DOI: https://doi.org/10.21741/9781644902813-96

The article was published as article 96 of the book Aeronautics and Astronautics

Content from this work may be used under the terms of the Creative Commons Attribution 3.0 license. Any further distribution of this work must maintain attribution to the author(s) and the title of the work, journal citation and DOI.

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