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

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dc.contributor.author Huete Ruiz de Lira, César
dc.contributor.author Urzay Lobo, Javier
dc.contributor.author Sánchez Pérez, Antonio Luis
dc.contributor.author Forman, Williams A.
dc.date.accessioned 2021-05-20T10:04:43Z
dc.date.available 2021-05-20T10:04:43Z
dc.date.issued 2016-03
dc.identifier.bibliographicCitation AIAA Journal, 54(3), March 2016, Pp. 962-975
dc.identifier.issn 0001-1452
dc.identifier.issn 1533-385X (online)
dc.identifier.uri http://hdl.handle.net/10016/32700
dc.description.abstract This 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.
dc.description.sponsorship This 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.
dc.format.extent 14
dc.language.iso eng
dc.publisher American Institute of Aeronautics and Astronautics, Inc.
dc.rights © 2015 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
dc.subject.other Propulsion
dc.subject.other Boundary layer analysis
dc.subject.other Adverse pressure gradient
dc.subject.other Supersonic flow
dc.subject.other Supersonic combustion
dc.subject.other Viscosity
dc.subject.other Thermal diffusivity
dc.subject.other Applied mathematics
dc.subject.other Flame holder
dc.subject.other Freestream Mach Number
dc.title Weak-shock interactions with transonic laminar mixing layers of fuels for high-speed propulsion
dc.type article
dc.subject.eciencia Ingeniería Industrial
dc.subject.eciencia Aeronáutica
dc.identifier.doi https://doi.org/10.2514/1.J054419
dc.rights.accessRights openAccess
dc.type.version acceptedVersion
dc.identifier.publicationfirstpage 962
dc.identifier.publicationissue 3
dc.identifier.publicationlastpage 975
dc.identifier.publicationtitle AIAA JOURNAL
dc.identifier.publicationvolume 54
dc.identifier.uxxi AR/0000027286
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