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

Result code in 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>
Result on the web
<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>

Result language
angličtina
Original language name
Active Flow Separation Control Applied at Wing-Pylon Junction of a Wing Section in Landing Configuration
Original language description
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.
Czech name
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Czech description
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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
2017
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Article name in the collection
AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
ISBN
978-1-62410-447-3
ISSN
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e-ISSN
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Number of pages
11
Pages from-to
nestrankovano
Publisher name
American Institute of Aeronautics and Astronautics Inc.
Place of publication
Neuveden
Event location
Grapevine, USA
Event date
Jan 9, 2017
Type of event by nationality
WRD - Celosvětová akce
UT code for WoS article
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