Etude de l' interaction choc/choc é des écoulements dans une tuyère. / Hamza Gouidmi  

Public ISBD Titre : Etude de l' interaction choc/choc é des écoulements dans une tuyère. Type de document : texte imprimé Auteurs : Hamza Gouidmi, Auteur ; Abdelhadi Beghidja, Directeur de thèse Editeur : جامعة الإخوة منتوري قسنطينة Année de publication : 2015 Importance : 191 f. Format : 30 cm. Note générale : 2 copies imprimes disponibles Langues : Français (fre) Catégories : Français - Anglais Génie Mécanique Tags : Tuyère supersonique  interaction choc/ choc  choc/ couche limite turbulente ou laminaire  injection secondaire  vectorisation fluidique  supersonic nozzle, shock/shock interaction  shock wave/turbulent or laminar boundary layer  secondary injection, fluidic vectoring  :فوھات الأسرع من الصوت، تداخل صدمة مع صدمة وصدمة مع الطبقة الحدودیة المضطربة أوالصفائحیة، تغییراتجاه السائل بواسطة مائع، الحقن الثانوي Index. décimale : 620 Génie Mécanique Résumé : In supersonic aerodynamics, the interaction phenomena shock/shock and shock/boundary layer, impose physical crucial problems in practical flow configurations. They are encountered in the intakes supersonic air, nozzle Rocket engines and supersonic air inlets. In this work, several numerical calculations were made touching directly the bottom of those interaction phenomena in the above mentioned configurations. They are based on solving stationary Navier-Stokes equations and quasi-stationary compressible supersonic flows, laminar and turbulent, using the FLUENT commercial. These numerical calculations were conducted for multiple configurations at different Mach numbers and pressure and injection ratios (NPR and SPR respectively). These parameters are directly affecting shock interaction phenomena. The results show different shock configurations according to the parameters mentioned above. An interaction zone on a flat plate of overall large in laminar calculation than in turbulent one and a set of shocks in the divergent nozzle with and without secondary injection have been highlighted. These results are generally consistent with those found experimentally and numerically. Diplôme : Doctorat en sciences En ligne : ../theses/gmecanique/GOU6850.pdf Format de la ressource électronique : pdf Permalink : index.php?lvl=notice_display&id=10147 Etude de l' interaction choc/choc é des écoulements dans une tuyère. [texte imprimé] / Hamza Gouidmi, Auteur ; Abdelhadi Beghidja, Directeur de thèse . - جامعة الإخوة منتوري قسنطينة, 2015 . - 191 f. ; 30 cm. 2 copies imprimes disponibles Langues : Français (fre) Catégories : Français - Anglais Génie Mécanique Tags : Tuyère supersonique  interaction choc/ choc  choc/ couche limite turbulente ou laminaire  injection secondaire  vectorisation fluidique  supersonic nozzle, shock/shock interaction  shock wave/turbulent or laminar boundary layer  secondary injection, fluidic vectoring  :فوھات الأسرع من الصوت، تداخل صدمة مع صدمة وصدمة مع الطبقة الحدودیة المضطربة أوالصفائحیة، تغییراتجاه السائل بواسطة مائع، الحقن الثانوي Index. décimale : 620 Génie Mécanique Résumé : In supersonic aerodynamics, the interaction phenomena shock/shock and shock/boundary layer, impose physical crucial problems in practical flow configurations. They are encountered in the intakes supersonic air, nozzle Rocket engines and supersonic air inlets. In this work, several numerical calculations were made touching directly the bottom of those interaction phenomena in the above mentioned configurations. They are based on solving stationary Navier-Stokes equations and quasi-stationary compressible supersonic flows, laminar and turbulent, using the FLUENT commercial. These numerical calculations were conducted for multiple configurations at different Mach numbers and pressure and injection ratios (NPR and SPR respectively). These parameters are directly affecting shock interaction phenomena. The results show different shock configurations according to the parameters mentioned above. An interaction zone on a flat plate of overall large in laminar calculation than in turbulent one and a set of shocks in the divergent nozzle with and without secondary injection have been highlighted. These results are generally consistent with those found experimentally and numerically. Diplôme : Doctorat en sciences En ligne : ../theses/gmecanique/GOU6850.pdf Format de la ressource électronique : pdf Permalink : index.php?lvl=notice_display&id=10147

Exemplaires (1)

Code-barres	Cote	Support	Localisation	Section	Disponibilité
GOU/6850	GOU/6850	Thèse	Bibliothèque principale	Thèses	Disponible

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