Active flow separation control at the outer wing

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F19%3AN0000044" target="_blank" >RIV/00010669:_____/19:N0000044 - isvavai.cz</a>

Výsledek na webu

<a href="https://link.springer.com/article/10.1007%2Fs13272-019-00402-4" target="_blank" >https://link.springer.com/article/10.1007%2Fs13272-019-00402-4</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1007/s13272-019-00402-4" target="_blank" >10.1007/s13272-019-00402-4</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Active flow separation control at the outer wing

Popis výsledku v původním jazyce

Within the European project AFLoNext, one of the technological streams is dedicated to the investigation of active flow control (AFC) to increase the robustness of the wing tip design at takeoff conditions, whilst allowing the optimization of aerodynamic efficiency in cruise. AFC is used to delay the wing tip stall, which is caused by vortex breakdown, thus improving the lift to drag ratio and allowing a steeper climb gradient during second segment climb when the landing gear is retracted. The numerical parametric studies of AFC aerodynamic sizing were shared between the involved partners on the basis of actuator location (in the leading edge region or on the upper surface) and actuator types (steady blowing, synthetic jets, pulsed jets). Most of the numerical results have been obtained for steady blowing through continuous or segmented slots. The specific effect of the unsteady means of actuation on the flow topology was also identified. The aim of this study was to take into account industrial requirements defined by Airbus and geometric constraints of AFC actuators arising from the project partners involved in the development of AFC hardware. Some comparisons between the partners’ results are presented, allowing preliminary conclusions to be drawn. The most effective and efficient device turned out to be pulsed blowing through segmented slots located at the leading edge separation line.

Název v anglickém jazyce

Active flow separation control at the outer wing

Popis výsledku anglicky

Within the European project AFLoNext, one of the technological streams is dedicated to the investigation of active flow control (AFC) to increase the robustness of the wing tip design at takeoff conditions, whilst allowing the optimization of aerodynamic efficiency in cruise. AFC is used to delay the wing tip stall, which is caused by vortex breakdown, thus improving the lift to drag ratio and allowing a steeper climb gradient during second segment climb when the landing gear is retracted. The numerical parametric studies of AFC aerodynamic sizing were shared between the involved partners on the basis of actuator location (in the leading edge region or on the upper surface) and actuator types (steady blowing, synthetic jets, pulsed jets). Most of the numerical results have been obtained for steady blowing through continuous or segmented slots. The specific effect of the unsteady means of actuation on the flow topology was also identified. The aim of this study was to take into account industrial requirements defined by Airbus and geometric constraints of AFC actuators arising from the project partners involved in the development of AFC hardware. Some comparisons between the partners’ results are presented, allowing preliminary conclusions to be drawn. The most effective and efficient device turned out to be pulsed blowing through segmented slots located at the leading edge separation line.

Druh

J_SC - Článek v periodiku v databázi SCOPUS

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/7E13056" target="_blank" >7E13056: 2nd Generation Active Wing – Active Flow- Loads & Noise control on next generation wing</a><br>

Návaznosti

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

Rok uplatnění

2019

Kód důvěrnosti údajů

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

Název periodika

CEAS Aeronautical Journal

ISSN

1869-5582

e-ISSN

1869-5590

Svazek periodika

neuveden

Číslo periodika v rámci svazku

22 June 2019

Stát vydavatele periodika

AT - Rakouská republika

Počet stran výsledku

14

Strana od-do

nestrankovano

Kód UT WoS článku

—

EID výsledku v databázi Scopus

2-s2.0-85068124572