Treffer: Numerical investigation of supersonic nozzle flow separation
Title:
Numerical investigation of supersonic nozzle flow separation
Authors:
Source:
AIAA journal. 45(3):532-541
Publisher Information:
Reston, VA: American Institute of Aeronautics and Astronautics, 2007.
Publication Year:
2007
Physical Description:
print, 20 ref
Original Material:
INIST-CNRS
Subject Terms:
Aeronautics astronautics, Aéronautique, astronautique, Mechanics acoustics, Mécanique et acoustique, Transportation, Transports, Sciences exactes et technologie, Exact sciences and technology, Physique, Physics, Domaines classiques de la physique (y compris les applications), Fundamental areas of phenomenology (including applications), Mécanique des fluides, Fluid dynamics, Méthodes de calcul en mécanique des fluides, Computational methods in fluid dynamics, Ecoulements compressibles; phénomènes de chocs et de détonation, Compressible flows; shock and detonation phenomena, Interactions des ondes de choc et effets de choc, Shock-wave interactions and shock effects, Ecoulements dans les tubes, les canaux et les conduites, Flows in ducts, channels, nozzles, and conduits, Convergence numérique, Numerical convergence, Convergencia numérica, Décollement écoulement, Flow separation, Détente, Gas expansion, Expansión gas, Ecoulement supersonique, Supersonic flow, Equation Navier Stokes, Navier-Stokes equations, Génération maille, Mesh generation, Modélisation, Modelling, Onde choc, Shock waves, Onde compression, Compressional waves, Simulation numérique, Digital simulation, Structure turbulence, Turbulence structure, Estructura turbulencia, Tuyère convergente divergente, Convergent divergent nozzle, Tobera convergente divergente, 4740N
Time:
4711, 4760
Document Type:
Konferenz
Conference Paper
File Description:
text
Language:
English
Author Affiliations:
National University of Singapore, Singapore 119260, Singapore
University of California, Irvine, Irvine, California 92697-3975, United States
University of California, Irvine, Irvine, California 92697-3975, United States
ISSN:
0001-1452
Rights:
Copyright 2007 INIST-CNRS
CC BY 4.0
Sauf mention contraire ci-dessus, le contenu de cette notice bibliographique peut être utilisé dans le cadre d’une licence CC BY 4.0 Inist-CNRS / Unless otherwise stated above, the content of this bibliographic record may be used under a CC BY 4.0 licence by Inist-CNRS / A menos que se haya señalado antes, el contenido de este registro bibliográfico puede ser utilizado al amparo de una licencia CC BY 4.0 Inist-CNRS
CC BY 4.0
Sauf mention contraire ci-dessus, le contenu de cette notice bibliographique peut être utilisé dans le cadre d’une licence CC BY 4.0 Inist-CNRS / Unless otherwise stated above, the content of this bibliographic record may be used under a CC BY 4.0 licence by Inist-CNRS / A menos que se haya señalado antes, el contenido de este registro bibliográfico puede ser utilizado al amparo de una licencia CC BY 4.0 Inist-CNRS
Notes:
Physics: fluid mechanics
Accession Number:
edscal.18624924
Database:
PASCAL Archive
Weitere Informationen
Separation of supersonic flow in a planar convergent-divergent nozzle with moderate expansion ratio is investigated by solving the Reynolds-averaged Navier-Stokes equations with a two-equation k-w turbulence model. The focus of the study is on the structure of the fluid and wave phenomena associated with the flow separation. Computations are conducted for an exit-to-throat area ratio of 1.5 and for a range of nozzle pressure ratios. The results are compared with available experimental data in a nozzle of the same geometry. The flow separates by the action of a lambda shock, followed by a succession of expansion and compression waves.