Numerical studies of active flow control on wing tip extension

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F19%3AN0000041" target="_blank" >RIV/00010669:_____/19:N0000041 - isvavai.cz</a>

Result on the web

<a href="https://www.emerald.com/insight/content/doi/10.1108/AEAT-01-2018-0053/full/html" target="_blank" >https://www.emerald.com/insight/content/doi/10.1108/AEAT-01-2018-0053/full/html</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1108/AEAT-01-2018-0053" target="_blank" >10.1108/AEAT-01-2018-0053</a>

Result language

angličtina

Original language name

Numerical studies of active flow control on wing tip extension

Original language description

In the European project AFLoNext, active flow control (AFC) measures were adopted in the wing tip extension leading edge to suppress flow separation. It is expected that the designed wing tip extension may improve aerodynamic efficiency by about 2 per cent in terms of fuel consumption and emissions. As the leading edge of the wing tip is not protected with high-lift device, flow separation occurs earlier than over the inboard wing in the take-off/landing configuration. The aim of this study is the adoption of AFC to delay wing tip stall and to improve lift-to-drag ratio. Several actuator locations and AFC strategies were tested with computational fluid dynamics. The first approach was “standard” one with physical modeling of the actuators, and the second one was focused on the volume forcing method. The actuators location and the forcing plane close to separation line of the reference configuration were chose to enhance the flow with steady and pulsed jet blowing. Dependence of the lift-to-drag benefit with respect to injected mass flow is investigated. The mechanism of flow separation onset is identified as the interaction of slat-end and wing tip vortices. These vortices moving toward each other with increasing angle of attack (AoA) interact and cause the flow separation. AFC is applied to control the slat-end vortex and the inboard movement of the wing tip vortex to suppress their interaction. The separation onset has been postponed by about 2° of AoA; the value of ift-to-drag (L/D) was improved up to 22 per cent for the most beneficial cases. The AFC using the steady or pulsed blowing (PB) was proved to be an effective tool for delaying the flow separation. Although better values of L/D have been reached using steady blowing, it is also shown that PB case with a duty cycle of 0.5 needs only one half of the mass flow. Two approaches of different levels of complexity are studied and compared. The first is based on physical modeling of actuator cavities, while the second relies on volume forcing method which does not require detailed actuator modeling. Both approaches give consistent results.

Czech name

—

Czech description

—

Type

J_imp - Article in a specialist periodical, which is included in the Web of Science database

CEP classification

—

OECD FORD branch

20304 - Aerospace engineering

Project

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

Continuities

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

Publication year

2019

Confidentiality

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

Name of the periodical

Aircraft Engineering and Aerospace Technology

ISSN

1748-8842

e-ISSN

1758-4213

Volume of the periodical

91

Issue of the periodical within the volume

2

Country of publishing house

GB - UNITED KINGDOM

Number of pages

7

Pages from-to

346-352

UT code for WoS article

000462372400016

EID of the result in the Scopus database

2-s2.0-85060182839