Relevant bibliographies by topics / Transsonika

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Transsonika'

Author: Grafiati
Published: 4 June 2021
Last updated: 15 February 2022

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Journal articles on the topic "Transsonika"

1

Lotova, N. A. "The solar wind transsonic region." Solar Physics 117, no. 2 (1988): 399–406. http://dx.doi.org/10.1007/bf00147255.

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Adarchenko, V. A., and S. M. Voronin. "Transsonic accretion modes with density jumps." Doklady Physics 60, no. 8 (August 2015): 333–37. http://dx.doi.org/10.1134/s1028335815080017.

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Goedbloed, J. P>. "Transsonic Instabilities in Laboratory and Astrophysical Plasmas." Physica Scripta T107, no. 5 (2004): 159. http://dx.doi.org/10.1238/physica.topical.107a00159.

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Kolesnik, Igor G., and Yaroslav Yu Ohul'chansky. "Hierarchical fragmented structure of molecular clouds produced by supersonic turbulence." Symposium - International Astronomical Union 147 (1991): 445–46. http://dx.doi.org/10.1017/s0074180900199346.

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For GMC's the two prominent properties are typical. They consist of dense molecular gas clumps concentrating to the GMC centre and filling only a few percent of a total volume. And these clumps participate in chaotic motions with velocities vt exceeding as a rule the sound velocity co at the temperature of molecular gas. This phenomenon is considered as a supersonic molecular cloud's turbulence. The compressibility of turbulent matter becomes very important with such velocities. Thus in application to GMC it is necessary to develop the theory of turbulence and fragmentation under transsonic and supersonic random motions. The hydrodynamic flow velocity field can be divided into the potential and vortical components. When transsonic or supersonic motions prevail the potential component is become more important that stimulates the shock wave's stochastic field development. Ohul'chansky (1988, Kinematics and Physics of Celestial Bodies 4,3) has described this process on the base of Burgers' equation treatment. In this paper we apply this approach for conditions of GMCs that permit the supersonic turbulence' spectrum evolution, the large density fluctuations development, and clumps formation to consider.
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Kolesnik, Igor G., and Yaroslav Yu Ohul'chansky. "Hierarchical fragmented structure of molecular clouds produced by supersonic turbulence." Symposium - International Astronomical Union 147 (1991): 445–46. http://dx.doi.org/10.1017/s007418090023996x.

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For GMC's the two prominent properties are typical. They consist of dense molecular gas clumps concentrating to the GMC centre and filling only a few percent of a total volume. And these clumps participate in chaotic motions with velocities vt exceeding as a rule the sound velocity co at the temperature of molecular gas. This phenomenon is considered as a supersonic molecular cloud's turbulence. The compressibility of turbulent matter becomes very important with such velocities. Thus in application to GMC it is necessary to develop the theory of turbulence and fragmentation under transsonic and supersonic random motions. The hydrodynamic flow velocity field can be divided into the potential and vortical components. When transsonic or supersonic motions prevail the potential component is become more important that stimulates the shock wave's stochastic field development. Ohul'chansky (1988, Kinematics and Physics of Celestial Bodies 4,3) has described this process on the base of Burgers' equation treatment. In this paper we apply this approach for conditions of GMCs that permit the supersonic turbulence' spectrum evolution, the large density fluctuations development, and clumps formation to consider.
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Fürst, J., and K. Kozel. "Numerical Solution of the Transsonic Flows through a Turbine Cascade." PAMM 1, no. 1 (March 2002): 524. http://dx.doi.org/10.1002/1617-7061(200203)1:1<524::aid-pamm524>3.0.co;2-b.

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Turolla, Roberto, and Luciano Nobili. "On the role of viscosity in spherically symmetric transsonic flows." Astrophysical Journal 342 (July 1989): 982. http://dx.doi.org/10.1086/167655.

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Lotova, N. A., and Ya V. Nagelys. "The investigation of the solar wind transsonic region at meter wavelengths." Solar Physics 117, no. 2 (1988): 407–14. http://dx.doi.org/10.1007/bf00147256.

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Jacquet, M. J., T. Boulier, F. Claude, A. Maître, E. Cancellieri, C. Adrados, A. Amo, et al. "Polariton fluids for analogue gravity physics." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 378, no. 2177 (July 20, 2020): 20190225. http://dx.doi.org/10.1098/rsta.2019.0225.

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Analogue gravity enables the study of fields on curved space–times in the laboratory. There are numerous experimental platforms in which amplification at the event horizon or the ergoregion has been observed. Here, we demonstrate how optically generating a defect in a polariton microcavity enables the creation of one- and two-dimensional, transsonic fluid flows. We show that this highly tuneable method permits the creation of horizons. Furthermore, we present a rotating geometry akin to the water-wave bathtub vortex. These experiments usher in the possibility of observing stimulated as well as spontaneous amplification by the Hawking, Penrose and Zeld’ovich effects in fluids of light. This article is part of a discussion meeting issue ‘The next generation of analogue gravity experiments’.
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DiFranco, Jeffery C., Peter D. Miller, and Benson K. Muite. "On the modified nonlinear schrödinger equation in the semiclassical limit: supersonic, subsonic, and transsonic behavior." Acta Mathematica Scientia 31, no. 6 (November 2011): 2343–77. http://dx.doi.org/10.1016/s0252-9602(11)60405-0.

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Dissertations / Theses on the topic "Transsonika"

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Kóňa, Marián. "Aerodynamický návrh transsonického bezpilotního kluzáku." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232008.

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This master thesis is focused on aerodynamic design of transonic glider, which is assigned for following an airliner at cruising regime of flight. Main goal of the thesis is to determine basic geometrical design of airplane with respect to Whitcomb aera rule, mass analysis and drag polar. Weight analysis includes determining center of gravity according to longitudinal static stability margin. The drag polar of the airplane is determine for cruising regime of flight, that means the regime of following an airliner.
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Hilgenfeld, Lothar. "Turbulenzstrukturen in hochbelasteten Transsonik-Verdichtergittern unter besonderer Berücksichtigung der Verdichtungsstoß-Grenzschicht-Interferenz." kostenfrei, 2006. http://nbn-resolving.de/urn:nbn:de:bvb:706-1840.

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Hilgenfeld, Lothar. "Turbulenzstrukturen in hochbelasteten Transsonik-Verdichtergittern unter besonderer Berücksichtigung der Verdichtungsstoss-Grenzschicht-Interferenz /." Düsseldorf : VDI-Verl, 2007. http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&doc_number=015516938&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA.

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Doupník, Petr. "Využití optimalizačních metod při návrhu transsonického křídla s implementací základních konstrukčně pevnostních omezení." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-233939.

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The thesis gives overview of complex aerodynamic optimization approach applied to business-jet aircraft wing design. Response surface method (RSM) potential was explored particularly. The efficiency of RSM approach for CFD based aerodynamic optimization was demonstrated. Basic structural requirements were successfully integrated to optimization – real multidisciplinary problem was solved. Some methods for evaluation of forces distribution along wingspan were explored. Thesis was solving within the frame of 6th EU FP integrated project CESAR.
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Philit, Mickaël. "Modélisation, simulation et analyse des instationnarités en écoulement transsonique décollé en vue d'application à l'aéroélasticité des turbomachines." Thesis, Ecully, Ecole centrale de Lyon, 2013. http://www.theses.fr/2013ECDL0033/document.

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Dans la conception des turbomachines modernes, la prédiction des phénomènes aéroélastiques est devenue un point clé. La tendance à réduire la masse et à augmenter la charge des composants aérodynamiques accroit le risque de rupture. Dans un tel contexte, la compréhension et la bonne prédiction des diverses instabilités constituent un enjeu industriel et scientifique majeur. Le présent travail de recherche a pour objectif d’améliorer la prédiction des phénomènes instationnaires intervenant dans les problèmes d’aéroélasticité en turbomachines. Cette thèse est plus particulièrement axée sur la simulation de l’interaction onde de choc/couche limite. Le support d’étude est une tuyère transsonique présentant un écoulement avec des zones décollées. L’oscillation forcée de l’onde de choc est simulée grâce à une méthode de petites perturbations instationnaires couplée avec une hypothèse de turbulence variable. Cette approche est validée par comparaison avec des mesures. Elle permet une prédiction tout à fait satisfaisante du premier harmonique de pression sur la paroi de la tuyère. Ce travail a montré la nécessité de linéariser le modèle de turbulence. Le besoin de dériver le modèle de turbulence nous a amené à investiguer la modélisation faite pour prédire l’interaction onde de choc/couche limite. Un modèle de turbulence à deux équations complété par une équation de « retard » est implémenté afin de capter un déséquilibre de la turbulence. Les résultats obtenus en tuyère sont cohérents avec la théorie mais une surproduction d’énergie turbulente en présence de bord d’attaque rend le modèle inefficace pour des configurations de turbomachines. Au final, l’introduction d’un limiteur de viscosité turbulente dans un modèle de turbulence à deux équations s’avère donner de bons résultats. La méthode de dérivation du modèle est alors présentée sur le modèle de Wilcox proposé en 2008. Enfin, la technique de linéarisation est étendue à la problématique aéroélastique. Une approche de couplage fluide-structure faible est adoptée. L’oscillation structurelle des aubages suivant les modes propres est considérée mais en laissant la fréquence évoluer au cours du couplage. La nouvelle méthode utilisée s’appuie sur la construction d’un méta-modèle du comportement dynamique du fluide afin de résoudre directement le système fluide-structure couplé. Cette technique est validée sur une configuration de grille annulaire de turbine en haut subsonique et présente l’avantage d’un temps de calcul réduit
In modern turbomachinery design, predicting aerolastic phenomena has become a key point. The development of highly loaded components, while reducing their weight, increases the risk of failure. In this context, good understanding and prediction of various instabilities are a major industrial and scientific challenge. This research work aims to improve the prediction of unsteady phenomena involved in turbomachinery aeroelasticity. This study focuses especially on the simulation of shock wave/boundary layer interaction. To begin with, a transonic nozzle separated flow is investigated. Forced oscillation of the shock wave system is simulated through a small unsteady perturbation method combined with the assumption of variable turbulence. This approach is validated against exprimental measurements. The first harmonic of pressure on the wall of the nozzle is predicted quite satisfactorily. The need to linearize the turbulence model was shown of high importance. Deriving the turbulence model, leads us to investigate the turbulence modeling performed to predict the shockwave/boundary layer interaction. A two equations turbulence model supplemented by a "time-lagged" equation is implemented to capture non-equilibrium effects of turbulence. All achieved results for a nozzle are consistent with theory, but overproduction of turbulent kinetic energy at leading edge makes the model useless for turbomachinery configurations. However, the introduction of an eddy viscosity stress limiter inside a two-equation turbulence model proves to give good results. The derivation method is thus presented on such a model, precisely on Wilcox model proposed in 2008. Finally, the linearization technique is extended to aeroelastic problems. A loose fluid-structure coupling strategy is adopted. The structural oscillation of the blades is considered for eigen-modes but frequency is free to change during coupling resolution. The new approach is based on the building of a meta-model to describe the fluid dynamic behavior in order to solve directly the coupled fluid-structure system. This technique is validated on a standard high subsonic turbine configuration and takes advantage of a reduced computation time
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Hilgenfeld, Lothar [Verfasser]. "Turbulenzstrukturen in hochbelasteten Transsonik-Verdichtergittern unter besonderer Berücksichtigung der Verdichtungsstoß-Grenzschicht-Interferenz / von Lothar Hilgenfeld." 2007. http://d-nb.info/983868948/34.

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Book chapters on the topic "Transsonika"

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Léal De Sousa, L., J. Duplex, and A. Caruso. "Extension of an Incompressible Algorithm for Compressible Flow Calculations; Validation on a Transsonic Flow in a Bump." In Notes on Numerical Fluid Mechanics (NNFM), 412–19. Wiesbaden: Vieweg+Teubner Verlag, 1998. http://dx.doi.org/10.1007/978-3-322-89859-3_45.

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Conference papers on the topic "Transsonika"

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Goedbloed, J. P. (Hans). "Transsonic instabilities in tokamaks and astrophysical accretion flows." In PLASMAS IN THE LABORATORY AND IN THE UNIVERSE: New Insights and New Challenges. AIP, 2004. http://dx.doi.org/10.1063/1.1718431.

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Roehl, C., and H. Simon. "Adaptive Unstructured Grids for Simulating Transsonic Flows in Turbomachinery." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-213.

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A method for simulations of the two-dimensional compressible flow in aerodynamically highly loaded turbomachinery on unstructured adaptive grids is presented in this paper. The discretization of the conservative laws in space is executed by the finite volume method. For high efficiency an implicit solution procedure is used. The flux vector of the inviscid flow is calculated by a modified difference splitting method described by Reichert and Simon (1994). To predict the turbulent flow an explicit algebraic stress model in conjunction with k and ε equations is used (Lenke and Simon, 1997). Both for the generation of the initial grid as well as for the grid adaptation the same algorithm is used which is based on the advancing-front method according to Peraire et.al. (1987). For the simulation of high Reynoldsnumber flow within thermal turbomachinery it is most favorable to use quadrilateral elements in the boundary layers in addition to the triangular elements in the main flow region. To adapt the so-called combined grids, some kind of key variables are chosen, e.g. change in total pressure in combination with a shock detector.
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Groll, Rodion, Fabian Fastabend, and Hans J. Rath. "Modelling Transsonic Flows Through Ring-Shape Thruster Geometries With DSMC." In ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/icnmm2012-73027.

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When modeling rarefied gas flows, continuous approximation is limited by the Knudsen regime. The presented cold gas thruster for space applications is investigated for pressure values lying between 10−2 and 103 Pa. It is comprised of a subsonic funnel region, a transsonic region consisting of a ring-shaped nozzle throat and a supersonic diffuser region. Diffusive and specular / mirror reflection is used to describe the behavior of particle/wall collision in the discrete model. Simulation results are compared both with experimental data and with numerical results computed using a finite-volume method. The transsonic flow through the nozzle throat shows very good agreement with experimental data. Simulation and experimental results emphasize the influence of various geometric factors like size and shape of the nozzle throat. Furthermore, differences in the acceleration behavior of Argon and Xenon are examined. Results of simulations utilizing the DSMC method [Bird, 1994, Stefanov et al., 2011] with diffusively reflecting boundary conditions present the best agreement with experimental data. Any deviation seen using the finite-volume method with no-slip boundary conditions can be explained by the equilibrium gas-state near the walls [Brenner, 2005, Greenshields et al., 2007]. The non-equilibrium approach produces lower velocity gradients near the wall, especially in wall regions with high levels of surface curvature.
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Zouganelis, I. "A new exospheric model of the solar wind acceleration: the transsonic solutions." In SOLAR WIND TEN: Proceedings of the Tenth International Solar Wind Conference. AIP, 2003. http://dx.doi.org/10.1063/1.1618602.

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Wilkosz, Benjamin, Markus Zimmermann, Philipp Schwarz, Peter Jeschke, and Caitlin Smythe. "Numerical Investigation of the Unsteady Interaction Within a Close-Coupled Centrifugal Compressor Used in an Aero Engine." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95644.

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The present work forms part of a research project of the Institute of Jet Propulsion and Turbomachinery at the RWTH Aachen University in collaboration with GE Aviation. The subject is the detailed numerical analysis of the unsteady flow field focusing on the interaction between the impeller and the passage diffuser of a close-coupled transsonic centrifugal compressor used in an aero engine. The centrifugal compressor investigated is characterized by a close-coupled impeller and passage diffuser with a radial gap of only 3.6%. The close coupling tends to provide a high aerodynamic efficiency but simultaneously cause a high unsteady interaction between the impeller and the diffuser. These unsteady effects can have a significant impact on the performance of both components [1,2] and present a challenge to state-of-the-art numerical methods. With increasing compressor efficiency, the more important it is to have a understanding of the detailed unsteady flow physics. Experimental data was obtained from a state-of-the art centrifugal compressor test rig located at the Institute of Jet Propulsion [3]. Steady and unsteady pressure measurements within the impeller and diffuser are used to gain detailed information on the temporal, time-averaged and spectral pressure distributions within the stage to validate the CFD. The work presented shows the unsteady phenomena caused by the interaction as well as the location and propagation of these phenomena within the centrifugal stage. Within the impeller, the exducer is in first order excited by the BPF of the diffuser, whereas in the diffuser both the BPF, as well as the PPF, are present up until the end of the pipe-diffuser. Significant effects on the integral component performance could only be identified for the impeller. Special focus is paid to evaluate the diffuser upstream pressure field, since this is the major source of unsteadiness within the impeller. The performance of the rotor decreases due to the unsteady interaction. This effect is traced back to the unsteady tip-clearance flow, in which the time-averaged mass transport decreases, whereas the specific entropy production increases in a nonlinear way. Within the diffuser, local effects counteracting with respect to the integral performance are found. In front of the throat, there is less decay in total pressure, as a result of tangentially expanding pressure waves. Within the passage an decrease in flow uniformity in the unsteady flow is identified as the reason for the lower diffusion up until the throat and higher losses within the downstream diffuser passage.
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