Airfoil leading edge blowing to control bow shock waves

Abstract This manuscript presents a detailed characterization of active control of bow shock waves via leading edge injection, including subsonic coolant ejection and the appearance of Coanda effects. The flow phenomena occurring at steady and pulsating flow injection regimes were analyzed using ste...

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Autores principales:	Francisco Lozano, Guillermo Paniagua
Formato:	article
Lenguaje:	EN
Publicado:	Nature Portfolio 2020
Materias:	Medicine R Science Q
Acceso en línea:	https://doaj.org/article/0e632f3d32864c6fa2ee44e729300b0c
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spelling	oai:doaj.org-article:0e632f3d32864c6fa2ee44e729300b0c2021-12-02T13:34:00ZAirfoil leading edge blowing to control bow shock waves10.1038/s41598-020-79048-w2045-2322https://doaj.org/article/0e632f3d32864c6fa2ee44e729300b0c2020-12-01T00:00:00Zhttps://doi.org/10.1038/s41598-020-79048-whttps://doaj.org/toc/2045-2322Abstract This manuscript presents a detailed characterization of active control of bow shock waves via leading edge injection, including subsonic coolant ejection and the appearance of Coanda effects. The flow phenomena occurring at steady and pulsating flow injection regimes were analyzed using steady and unsteady two-dimensional Reynolds-Averaged Navier Stokes, leading to a precise evaluation of the thermal load and drag reductions. Steady supersonic injection yields the largest abatement in thermal load and aerodynamic drag, while subsonic or fluctuating ones can also provide significant improvements at reduced cooling mass flow rates. Furthermore, a Coanda effect, causing a non-symmetric flow topology, was observed and analyzed for reduced injection port size. This Coanda effect is due to the sudden expansion happening from the injection port to the main flow and it causes the flow topology at the leading edge to become non-symmetric despite the complete symmetry of the problem. This is the first time in the literature such a phenomenon is documented for a supersonic airfoil leading edge injection. Furthermore, it enables the design of novel flow control strategies for the leading edge shock topology and flow structures in supersonic flows.Francisco LozanoGuillermo PaniaguaNature PortfolioarticleMedicineRScienceQENScientific Reports, Vol 10, Iss 1, Pp 1-18 (2020)
institution	DOAJ
collection	DOAJ
language	EN
topic	Medicine R Science Q
spellingShingle	Medicine R Science Q Francisco Lozano Guillermo Paniagua Airfoil leading edge blowing to control bow shock waves
description	Abstract This manuscript presents a detailed characterization of active control of bow shock waves via leading edge injection, including subsonic coolant ejection and the appearance of Coanda effects. The flow phenomena occurring at steady and pulsating flow injection regimes were analyzed using steady and unsteady two-dimensional Reynolds-Averaged Navier Stokes, leading to a precise evaluation of the thermal load and drag reductions. Steady supersonic injection yields the largest abatement in thermal load and aerodynamic drag, while subsonic or fluctuating ones can also provide significant improvements at reduced cooling mass flow rates. Furthermore, a Coanda effect, causing a non-symmetric flow topology, was observed and analyzed for reduced injection port size. This Coanda effect is due to the sudden expansion happening from the injection port to the main flow and it causes the flow topology at the leading edge to become non-symmetric despite the complete symmetry of the problem. This is the first time in the literature such a phenomenon is documented for a supersonic airfoil leading edge injection. Furthermore, it enables the design of novel flow control strategies for the leading edge shock topology and flow structures in supersonic flows.
format	article
author	Francisco Lozano Guillermo Paniagua
author_facet	Francisco Lozano Guillermo Paniagua
author_sort	Francisco Lozano
title	Airfoil leading edge blowing to control bow shock waves
title_short	Airfoil leading edge blowing to control bow shock waves
title_full	Airfoil leading edge blowing to control bow shock waves
title_fullStr	Airfoil leading edge blowing to control bow shock waves
title_full_unstemmed	Airfoil leading edge blowing to control bow shock waves
title_sort	airfoil leading edge blowing to control bow shock waves
publisher	Nature Portfolio
publishDate	2020
url	https://doaj.org/article/0e632f3d32864c6fa2ee44e729300b0c
work_keys_str_mv	AT franciscolozano airfoilleadingedgeblowingtocontrolbowshockwaves AT guillermopaniagua airfoilleadingedgeblowingtocontrolbowshockwaves
_version_	1718392778794205184

Airfoil leading edge blowing to control bow shock waves

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