Littérature scientifique sur le sujet « Overexpanded flow »
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Articles de revues sur le sujet "Overexpanded flow"
Moore, J., et K. M. Elward. « Shock Formation in Overexpanded Tip Leakage Flow ». Journal of Turbomachinery 115, no 3 (1 juillet 1993) : 392–99. http://dx.doi.org/10.1115/1.2929266.
Texte intégralVerma, S. B., et Oskar Haidn. « Flow Characteristics of Overexpanded Rocket Nozzles ». International Journal of Aerospace Innovations 2, no 4 (décembre 2010) : 259–77. http://dx.doi.org/10.1260/1757-2258.2.4.259.
Texte intégralMIYAZATO, Yoshiaki, Masashi KASHITANI, Hiroshi KATANODA et Kazuyasu MATSUO. « Characteristics of Overexpanded Flow in a Supersonic Nozzle ». Journal of the Visualization Society of Japan 15, Supplement2 (1995) : 23–26. http://dx.doi.org/10.3154/jvs.15.supplement2_23.
Texte intégralChung, Chan-Hong, Kenneth J. De Witt, Robert M. Stubbs et Paul F. Penko. « Simulation of overexpanded low-density nozzle plume flow ». AIAA Journal 33, no 9 (septembre 1995) : 1646–50. http://dx.doi.org/10.2514/3.12812.
Texte intégralSilnikov, M. V., et M. V. Chernyshov. « Supersonic flow gradients at an overexpanded nozzle lip ». Shock Waves 28, no 4 (13 novembre 2017) : 765–84. http://dx.doi.org/10.1007/s00193-017-0772-2.
Texte intégralSharma, H., A. Vashishtha, E. Rathakrishnan et P. Lovaraju. « Experimental study of overexpanded co-flowing jets ». Aeronautical Journal 112, no 1135 (septembre 2008) : 537–46. http://dx.doi.org/10.1017/s0001924000002499.
Texte intégralSHIMSHI, E., G. BEN-DOR et A. LEVY. « Viscous simulation of shock-reflection hysteresis in overexpanded planar nozzles ». Journal of Fluid Mechanics 635 (10 septembre 2009) : 189–206. http://dx.doi.org/10.1017/s002211200900771x.
Texte intégralZebiri, B., A. Piquet, A. Hadjadj et S. B. Verma. « Shock-Induced Flow Separation in an Overexpanded Supersonic Planar Nozzle ». AIAA Journal 58, no 5 (mai 2020) : 2122–31. http://dx.doi.org/10.2514/1.j058705.
Texte intégralSatyajit, De, et Ethirajan Rathakrishnan. « Experimental study of supersonic co-flowing jet ». Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering 233, no 4 (9 janvier 2018) : 1237–49. http://dx.doi.org/10.1177/0954410017749866.
Texte intégralMoiseev, M. G., E. A. Nikulicheva et V. S. Suminova. « Convergent-Divergent Nozzle under Highly Overexpanded Conditions ». Fluid Dynamics 39, no 3 (mai 2004) : 503–10. http://dx.doi.org/10.1023/b:flui.0000038569.29058.7e.
Texte intégralThèses sur le sujet "Overexpanded flow"
Elward, Kevin M. « Shock formation in overexpanded flow : a study using the hydraulic analogy ». Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/45949.
Texte intégralTests were performed to study the mechanism of shock formation in supersonic flow in long orifices to gain insight into the leakage flow of turbine tip gaps. The flow was modeled on a water table using a sharp-edged rectangular channel. The hydraulic analogy between free surface water flows and compressible gas flows was used to study the implications of the water table flow on tip leakage flows.
The flow on the water table exhibited oblique hydraulic jumps starting on the channel sidewall near the channel entrance. This flow was analyzed using the oblique hydraulic jump relations developed by classical hydraulic theory. The results of this analysis suggested a model for the formation of the jump. As the flow accelerates around the corner of the channel entrance, supercritical free stream flow is turned as it intersects the sidewall. The abrupt change in flow direction results in the formation of the oblique hydraulic jump.
An acceptable hydraulic analogy of compressible gas flows with shocks was obtained by reducing the surface tension of the water and using a large model size. The modified analogy for non-isentropic flow then allowed quantitative evaluation of the modeled shock structure in a compressible flow field. The predicted shock formation in such a flow has possible implications for both the efficiency of a gas turbine and the useful life of the turbine blade.
Master of Science
Östlund, Jan. « Flow Processes in Rocket Engine Nozzles with Focus on Flow Separation and Side-Loads ». Licentiate thesis, KTH, Mechanics, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-1452.
Texte intégralÖstlund, Jan. « Supersonic flow separation with application to rocket engine nozzles ». Doctoral thesis, KTH, Mechanics, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3793.
Texte intégralThe increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in fullscale, due to the uncertainties involved in modeling andpredicting the flow phenomena involved.
In the present work the causes of unsteady and unsymmetricalflow separation and resulting side-loads in rocket enginenozzles are investigated. This involves the use of acombination of analytical, numerical and experimental methods,which all are presented in the thesis. A main part of the workis based on sub-scale testing of model nozzles operated withair. Hence, aspects on how to design sub-scale models that areable to capture the relevant physics of full-scale rocketengine nozzles are highlighted. Scaling laws like thosepresented in here are indispensable for extracting side-loadcorrelations from sub-scale tests and applying them tofull-scale nozzles.
Three main types of side-load mechanisms have been observedin the test campaigns, due to: (i) intermittent and randompressure fluctuations, (ii) transition in separation patternand (iii) aeroelastic coupling. All these three types aredescribed and exemplified by test results together withanalysis. A comprehensive, up-to-date review of supersonic flowseparation and side-loads in internal nozzle flows is givenwith an in-depth discussion of different approaches forpredicting the phenomena. This includes methods for predictingshock-induced separation, models for predicting side-loadlevels and aeroelastic coupling effects. Examples are presentedto illustrate the status of various methods, and theiradvantages and shortcomings are discussed.
A major part of the thesis focus on the fundamentalshock-wave turbulent boundary layer interaction (SWTBLI) and aphysical description of the phenomenon is given. Thisdescription is based on theoretical concepts, computationalresults and experimental observation, where, however, emphasisis placed on the rocket-engineering perspective. This workconnects the industrial development of rocket engine nozzles tothe fundamental research of the SWTBLI phenomenon and shows howthese research results can be utilized in real applications.The thesis is concluded with remarks on active and passive flowcontrol in rocket nozzles and directions of futureresearch.
The present work was performed at VAC's Space PropulsionDivision within the framework of European spacecooperation.
Keywords:turbulent, boundary layer, shock wave,interaction, overexpanded,rocket nozzle, flow separation,control, side-load, experiments, models, review.
Zebiri, Boubakr. « Étude numérique des interactions onde de choc / couche limite dans les tuyères propulsives Shock-induced flow separation in an overexpanded supersonic planar nozzle A parallel high-order compressible flows solver with domain decomposition method in the generalized curvilinear coordinates system Analysis of shock-wave unsteadiness in conical supersonic nozzles ». Thesis, Normandie, 2020. http://www.theses.fr/2020NORMIR06.
Texte intégralThe need for a better understanding of the driving mechanism for the observed low-frequency unsteadiness in an over-expanded nozzle flows was discussed. The unsteady character of the shock wave/boundary layer remains an important practical challenge for the nozzle flow problems. Additionally, for a given incoming turbulent boundary layer, this kind of flow usually exhibits higher low-frequency shock motions which are less coupled from the timescales of the incoming turbulence. This may be good from an experimenter’s point of view, because of the difficulties in measuring higher frequencies, but it is more challenging from a computational point of view due to the need to obtain long time series to resolve low-frequency movements. In excellent agreement with the experimental findings, a very-long LES simulation run was carried out to demonstrate the existence of energetic broadband low-frequency motions near the separation point. Particular efforts were done in order to avoid any upstream low-frequency forcing, and it was explicitly demonstrated that the observed low-frequency shock oscillations were not connected with the inflow turbulence generation, ruling out the possibility of a numerical artefact. Different methods of spectral analysis and dynamic mode decomposition have been used to show that the timescales involved in such a mechanism are about two orders of magnitude larger than the time scales involved in the turbulence of the boundary layer, which is consistent with the observed low-frequency motions. Furthermore, those timescales were shown to be strongly modulated by the amount of reversed flow inside the separation bubble. This scenario can, in principle, explain both the low-frequency unsteadiness and its broadband nature
Sainte-Rose, Bruno. « Simulations numériques d'écoulements réactifs massivement décollés par une approche hybride RANS/LES ». Phd thesis, Ecole Centrale Paris, 2010. http://tel.archives-ouvertes.fr/tel-00635538.
Texte intégralChapitres de livres sur le sujet "Overexpanded flow"
GrÄsel, Jűrgen, et Alfred E. Beylich. « Enhanced Thrust-Efficiency of Overexpanded Nozzles by Passive Venting ». Dans IUTAM Symposium on Mechanics of Passive and Active Flow Control, 69–74. Dordrecht : Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4199-4_10.
Texte intégralSilnikov, M. V., M. V. Chernyshov et V. N. Uskov. « Overexpanded Jet Flow Theoretical Analysis in the Vicinity of the Nozzle Lip ». Dans 30th International Symposium on Shock Waves 1, 293–97. Cham : Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-46213-4_48.
Texte intégralMartelli, Emanuele, Barbara Betti, Francesco Nasuti et Marcello Onofri. « Effect of the Adiabatic Index on the Shock Reflection in Overexpanded Nozzle Flow ». Dans 30th International Symposium on Shock Waves 1, 89–93. Cham : Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-46213-4_14.
Texte intégralUskov, V. N., et M. V. Chernyshov. « Some special features of the flow in compressed layer downstream the incident shock in overexpanded jet ». Dans Shock Waves, 1509–14. Berlin, Heidelberg : Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_116.
Texte intégralSilnikov, M. V., et M. V. Chernyshov. « Overexpanded Jet Flow Type of Symmetry Influence on the Differential Characteristics of Flowfield in the Compressed Layer ». Dans Shock Wave Interactions, 57–71. Cham : Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-73180-3_4.
Texte intégralActes de conférences sur le sujet "Overexpanded flow"
Moore, John, et Kevin M. Elward. « Shock Formation in Overexpanded Tip Leakage Flow ». Dans ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-001.
Texte intégralZerjeski, David. « Semi-empirical Flow Separation Model For Overexpanded Rocket Nozzles ». Dans 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.iac-03-s.p.21.
Texte intégralReijasse, Ph, L. Morzenski, D. Blacodon et J. Birkemeyer. « Flow separation experimental analysis in overexpanded subscale rocket-nozzles ». Dans 37th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3556.
Texte intégralOstlund, Jan, et Mattias Jaran. « Assessment of turbulence models in overexpanded rocket nozzle flow simulations ». Dans 35th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2583.
Texte intégralXia, Yang, et R. Schwane. « CFD-Aided Aerodynamic Stability Analysis of an Overexpanded Rocket Nozzle Under the Influence of Unsteady Side Loads ». Dans 2nd AIAA Flow Control Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2418.
Texte intégralHamed, A., et C. Vogiatzis. « Assessment of turbulence models in overexpanded 2D-CD nozzle flow simulations ». Dans 31st Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2615.
Texte intégralHamed, A., C. Vogiatzis, A. Hamed et C. Vogiatzis. « Three dimensional flow computations and thrust predictions in 2DCD overexpanded nozzles ». Dans 35th Aerospace Sciences Meeting and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-30.
Texte intégralBen-Dor, G., I. Elperin, O. Igra et E. Vasiliev. « Gas-Solid Suspension Flow in a Nozzle and the Overexpanded Free Jet ». Dans ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-0773.
Texte intégralSchomberg, Kyll A., Graham Doig, John Olsen et Andrew J. Neely. « Geometric Analysis of the Linear Expansion-Deflection Nozzle at Highly Overexpanded Flow Conditions ». Dans 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-4001.
Texte intégralGirard, Sébastien, et Philippe Reijasse. « Effect of an internal shock wave on the flow patter in an overexpanded regime ». Dans 25th AIAA Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-3921.
Texte intégralRapports d'organisations sur le sujet "Overexpanded flow"
Liu, Junhui, Andrew Corrigan, K. Kailasanath, Nicholas Heeb et Ephraim Gutmark. Numerical Study of Noise Characteristics in Overexpanded Jet Flows. Fort Belvoir, VA : Defense Technical Information Center, août 2015. http://dx.doi.org/10.21236/ada625866.
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