Active Flow Separation Control Applied at Wing-Pylon Junction of a Wing Section in Landing Configuration

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F17%3AN0000038" target="_blank" >RIV/00010669:_____/17:N0000038 - isvavai.cz</a>

Výsledek na webu

<a href="https://arc.aiaa.org/doi/pdf/10.2514/6.2017-0491" target="_blank" >https://arc.aiaa.org/doi/pdf/10.2514/6.2017-0491</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.2514/6.2017-0491" target="_blank" >10.2514/6.2017-0491</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Active Flow Separation Control Applied at Wing-Pylon Junction of a Wing Section in Landing Configuration

Popis výsledku v původním jazyce

Synthetic Jets Actuators (SJA) that produce a zero net mass flow rate have been locally applied at the pylon-wing junction to suppress the local flow separation caused by the closely coupled Ultra-High Bypass Ratio engine integration. The high fidelity numerical simulations utilizing unsteady Reynolds-averaged Navier-Stokes solver have been performed to simulate this problem. A wind tunnel model representing a 2.5D wing with pylon, nacelle and deployed high-lift devices has been used for this study. Active Flow Control (AFC) applied at the wing-pylon junction area can prevent larger flow separation on the wing behind the nacelle caused by the slat cutback, increase the lift and to postpone the stall angle by interaction of the vortices from the SJA with vortices dominating this region. The performed unsteady CFD simulations demonstrate the possibility to locally affect the flow separation by utilization of AFC. The geometrical setup of the actuators (number and locations) and the flow parameters (blowing coefficient, actuation frequency and phase shift) have been varied, as well. Unsteady boundary conditions were used to simulate the effect of SJA. The positive effect of the application of the SJA on the lift and local flow separation has been observed.

Název v anglickém jazyce

Active Flow Separation Control Applied at Wing-Pylon Junction of a Wing Section in Landing Configuration

Popis výsledku anglicky

Synthetic Jets Actuators (SJA) that produce a zero net mass flow rate have been locally applied at the pylon-wing junction to suppress the local flow separation caused by the closely coupled Ultra-High Bypass Ratio engine integration. The high fidelity numerical simulations utilizing unsteady Reynolds-averaged Navier-Stokes solver have been performed to simulate this problem. A wind tunnel model representing a 2.5D wing with pylon, nacelle and deployed high-lift devices has been used for this study. Active Flow Control (AFC) applied at the wing-pylon junction area can prevent larger flow separation on the wing behind the nacelle caused by the slat cutback, increase the lift and to postpone the stall angle by interaction of the vortices from the SJA with vortices dominating this region. The performed unsteady CFD simulations demonstrate the possibility to locally affect the flow separation by utilization of AFC. The geometrical setup of the actuators (number and locations) and the flow parameters (blowing coefficient, actuation frequency and phase shift) have been varied, as well. Unsteady boundary conditions were used to simulate the effect of SJA. The positive effect of the application of the SJA on the lift and local flow separation has been observed.

Druh

D - Stať ve sborníku

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

2017

Kód důvěrnosti údajů

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

Název statě ve sborníku

AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting

ISBN

978-1-62410-447-3

ISSN

—

e-ISSN

—

Počet stran výsledku

11

Strana od-do

nestrankovano

Název nakladatele

American Institute of Aeronautics and Astronautics Inc.

Místo vydání

Neuveden

Místo konání akce

Grapevine, USA

Datum konání akce

9. 1. 2017

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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