Suppression of the separation zone by a spark discharge on laminar transonic airfoil

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Abstract

The effect of plasma actuators on Shock Wave / Laminar Boundary Layer Interaction (SWBLI) was studied experimentally on transonic laminar aerofoil. The steady and unsteady characteristics of the separation zone were measured for several flow regimes including the transonic buffet. Multi Sliding Spark Discharge was used for the flow control. Successful suppression of separated flow and laminar transonic buffet by plasma actuators' was demonstrated. An analysis of the discharge pulse energy effect on SWBLI was carried out. The perturbation and thermal spot evolution generated by the discharge was studied in the zone of SWBLI.

Original languageEnglish
Title of host publicationProceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017
Subtitle of host publicationDedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Editors Fomin
PublisherAmerican Institute of Physics Inc.
Number of pages16
Volume1893
ISBN (Electronic)9780735415782
DOIs
Publication statusPublished - 26 Oct 2017
Event25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017 - Novosibirsk, Russian Federation
Duration: 5 Jun 20179 Jun 2017

Publication series

NameAIP Conference Proceedings
PublisherAMER INST PHYSICS
Volume1893
ISSN (Print)0094-243X

Conference

Conference25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017
CountryRussian Federation
CityNovosibirsk
Period05.06.201709.06.2017

Keywords

  • FLOW

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