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Weak-shock interactions with transonic laminar mixing layers of fuels for high-speed propulsion

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dc.affiliation.dptoUC3M. Departamento de Ingeniería Térmica y de Fluidoses
dc.affiliation.grupoinvUC3M. Grupo de Investigación: Mecánica de Fluidoses
dc.contributor.authorHuete Ruiz de Lira, César
dc.contributor.authorUrzay Lobo, Javier
dc.contributor.authorSánchez Pérez, Antonio Luis
dc.contributor.authorForman, Williams A.
dc.date.accessioned2021-05-20T10:04:43Z
dc.date.available2021-05-20T10:04:43Z
dc.date.issued2016-03
dc.description.abstractThis paper extends to transonic mixing layers an analysis of Lighthill ("Reflection at a Laminar Boundary Layer of a Weak Steady Disturbance to a Supersonic Stream, Neglecting Viscosity and Heat Conduction," Quarterly Journal of Mechanics and Applied Mathematics, Vol. 54, No. 3, 1950, pp. 303-325.) on the interaction between weak shocks and laminar boundary layers. As in that work, the analysis is carried out under linear-inviscid assumptions for the perturbation field, with streamwise changes of the base flow neglected, as is appropriate given the slenderness of the mixing-layer flow. The steady-disturbance profile is determined by taking a Fourier transform along the longitudinal coordinate. Closed-form analytical functions for the pressure field are derived in the small- and large-wave-number limits, and vorticity disturbances are obtained as functions of the pressure perturbations. The analysis is particularized to ethylene&-air and hydrogen&-air mixing layers, for which the dynamics are of current interest for hypersonic propulsion. The results provide, in particular, the effective distance of upstream influence of the pressure perturbation in the subsonic stream. The resulting value, which scales with the thickness of the subsonic layer, is much smaller than the upstream influence distances encountered in boundary layers. This study may serve as a basis to understand shock-induced autoignition and flameholding phenomena in simplified versions of non-premixed supersonic-combustion problems.en
dc.description.sponsorshipThis work was supported by the U.S. Air Force Office of Scientific Research grants FA9550-12-1-0138 and FA9550-14-1-0219. We aregrateful to Amable Liñán for useful conversations at the early stages of this project.en
dc.format.extent14es
dc.identifier.bibliographicCitationAIAA Journal, 54(3), March 2016, Pp. 962-975en
dc.identifier.doihttps://doi.org/10.2514/1.J054419
dc.identifier.issn0001-1452
dc.identifier.issn1533-385X (online)
dc.identifier.publicationfirstpage962es
dc.identifier.publicationissue3es
dc.identifier.publicationlastpage975es
dc.identifier.publicationtitleAIAA JOURNALen
dc.identifier.publicationvolume54es
dc.identifier.urihttps://hdl.handle.net/10016/32700
dc.identifier.uxxiAR/0000027286
dc.language.isoengen
dc.publisherAmerican Institute of Aeronautics and Astronautics, Inc.en
dc.rights© 2015 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.en
dc.rights.accessRightsopen accessen
dc.subject.ecienciaIngeniería Industriales
dc.subject.ecienciaAeronáuticaes
dc.subject.otherPropulsionen
dc.subject.otherBoundary layer analysisen
dc.subject.otherAdverse pressure gradienten
dc.subject.otherSupersonic flowen
dc.subject.otherSupersonic combustionen
dc.subject.otherViscosityen
dc.subject.otherThermal diffusivityen
dc.subject.otherApplied mathematicsen
dc.subject.otherFlame holderen
dc.subject.otherFreestream Mach Numberes
dc.titleWeak-shock interactions with transonic laminar mixing layers of fuels for high-speed propulsionen
dc.typeresearch article*
dc.type.hasVersionAM*
dspace.entity.typePublication
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