Open AccessWing conceptual design for the airplane with distributed electric propulsion
Author(s) -
Pavel Hospodář,
Jan Klesa,
Nikola Žižkovský
Publication year - 2021
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/1024/1/012077
Subject(s) - wing , fuselage , aerodynamics , airplane , wing loading , wingspan , propulsion , aerospace engineering , fuel efficiency , engineering , wing twist , conceptual design , range (aeronautics) , washout , automotive engineering , structural engineering , mechanical engineering , angle of attack , physics , meteorology
This paper is focused on the usage of distributed electric propulsion (DEP) in order to increase aerodynamic efficiency. A ten seats aircraft is used as a case study. New design uses the existing fuselage, tail and turboprop engine, only wing is completely redesigned. The cost function for the design procedure consists of two parts. The first one is aerodynamic efficiency, which has a primary impact on fuel consumption, and the second one is weight of the wing. Lifting line theory with blade element momentum theory is used to design a wing geometry with DEP. Optimal geometry is also verified by CFD simulation. The estimation of the wing weight is needed for the second part of the cost function. This was done by the design of elementary wing parts under CS-23 regulation. The wing is assumed as full-aluminium with two spars. The main goal of this optimization is to redesign the wing for a given range and save as much fuel as possible.