Wing conceptual design for the airplane with distributed electric propulsion

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F21%3A00348082" target="_blank" >RIV/68407700:21220/21:00348082 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1088/issn.1757-899X" target="_blank" >https://doi.org/10.1088/issn.1757-899X</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1088/issn.1757-899X" target="_blank" >10.1088/issn.1757-899X</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Wing conceptual design for the airplane with distributed electric propulsion

Popis výsledku v původním jazyce

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.

Název v anglickém jazyce

Wing conceptual design for the airplane with distributed electric propulsion

Popis výsledku anglicky

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.

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/EF16_019%2F0000826" target="_blank" >EF16_019/0000826: Centrum pokročilých leteckých technologií</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2021

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

10th EASN International Conference on Innovation in Aviation & Space to the Satisfaction of the European Citizens

ISBN

—

ISSN

1757-899X

e-ISSN

1757-899X

Počet stran výsledku

6

Strana od-do

—

Název nakladatele

EDP Sciences

Místo vydání

—

Místo konání akce

virtual

Datum konání akce

2. 9. 2020

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

—