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Evaluation of miniature vortex generators for flow control in Falkner-Skan boundary layers
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.ORCID iD: 0000-0002-3251-8328
2016 (English)In: 54th AIAA Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics, 2016Conference paper, (Refereed)
Abstract [en]

Vortex generators with heights comparable to displacement thickness are an effective means of producing persistent mean-flow streaks in laminar boundary layers. Inducing streaky base flows can suppress growth of unsteady disturbances which would otherwise incite laminar-to-turbulent transition. Previous experimental and numerical works have demonstrated the versatility of these miniature vortex generators (MVGs) in zero pressure gradient boundary layers. In this work, mean-flow disturbances developing from MVGs in adverse and favorable pressure gradient boundary layers are measured systemically to assess the possibility of extending MVG-based flow control to these scenarios. Boundary-layer streak amplitudes are measured across a range of Falkner-Skan m values and an empirical scaling is found in congruence with existing results. The effect of streaks on transition in an adverse pressure gradient boundary layer is also tested and moderate increases to laminar flow extents are observed.

Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics, 2016.
Keyword [en]
Aerospace engineering, Aviation, Boundary layer flow, Boundary layers, Flow control, Laminar flow, Pressure gradient, Turbulent flow, Vortex flow, Adverse pressure gradient, Boundary layer streaks, Displacement thickness, Empirical scaling, Favorable pressure gradients, Laminar to turbulent transitions, Unsteady disturbance, Zero-pressure-gradient boundary layers, Laminar boundary layer
National Category
Applied Mechanics
Identifiers
URN: urn:nbn:se:kth:diva-201981Scopus ID: 2-s2.0-85007439486ISBN: 9781624103933 (print)OAI: oai:DiVA.org:kth-201981DiVA: diva2:1078329
Conference
54th AIAA Aerospace Sciences Meeting, 2016, 4 January 2016 through 8 January 2016
Note

Funding text: This work is part of the MOTSTRÖM project and is funded by VINNOVA through Nationella ygtekniska forskningsprogrammet (NFFP).

QC 20170303

Available from: 2017-03-03 Created: 2017-03-03 Last updated: 2017-03-03Bibliographically approved

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