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Wyszukujesz frazę "shock interaction" wg kryterium: Temat

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    Wyświetlanie 1-6 z 6
    Tytuł:
    Simulation of impact interaction of rail transport carriage in a butt roughness zone
    Autorzy:
    Shpachuk, Vladimir
    Chuprynin, Aleksandr
    Daleka, Vasily
    Suprun, Tatiana
    Powiązania:
    https://bibliotekanauki.pl/articles/197058.pdf
    Data publikacji:
    2020
    Wydawca:
    Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
    Tematy:
    four-axle carriage
    tram
    track
    carriage motion phase
    shock interaction
    butt roughness
    wózek czteroosiowy
    tramwaj
    tor
    faza ruchu wózka
    oddziaływanie uderzeniowe
    Opis:
    Mechanical and mathematical models of mechanical multidimensional discrete-continuous systems “carriage – track” in terms of static and impact interaction in a butt roughness zone are proposed. Their interaction is investigated with the example of a four-axle car and a track for four motion phases in the place of isolated butt roughness. Parameters of static and impact interaction of the carriage with a track in a place of butt joint which takes into account operational and constructive factors are defined.
    Źródło:
    Zeszyty Naukowe. Transport / Politechnika Śląska; 2020, 106; 141-152
    0209-3324
    2450-1549
    Pojawia się w:
    Zeszyty Naukowe. Transport / Politechnika Śląska
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The analysis of separation and methods of three-dimensional flow structure detection in the boundary layer shock wave interaction
    Autorzy:
    Czerwińska, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/1954539.pdf
    Data publikacji:
    1999
    Wydawca:
    Politechnika Gdańska
    Tematy:
    shock wave boundary layer interaction
    flow separation
    3D flow structures
    numerical simulations
    Opis:
    The normal shock wave turbulent boundary layer interaction still draws a great deal of attention as a flow phenomenon. This is due to its profound importance to numerous applications. The understanding of phenomena is crucial for future aims connected with the interaction control. Experimental investigations of the interaction have been carried out since the 1940s. They were aimed however at the determination of such general flow features as: pressure distribution, shock wave configuration or oil visualization of separation structures. In order to better understand the phenomenon, measurements of the entire field are required. At present, such measurements do not exist. A great help is expected from numerical simulations in this respect. There is enough experimental data to check the general features of the flow obtained from calculations. This thesis presents numerical simulations of flow that is assumed: steady, three-dimensional, compressible, viscous and turbulent. Its general aim is to present to what extend the modern numerical methods are able to predict the flow in shock wave turbulent boundary layer interaction including shock induced separation structures. These structures are very sensitive to channel geometry and may be useful in the understanding of separation's development. In order to illustrate the abilities of numerical simulations, one aim of the presented thesis is to investigate the effect of the span-wise depth of the nominally two-dimensional test section. The presented results cast some light on the common problems experienced by typical comparisons of two-dimensional simulations to wind tunnel tests having a three-dimensional nature. The first Chapter presents the basic theory of elementary structures. Considerations of elementary structures of the flow along with their dependencies are necessary for a better understanding of the separation flow structures induced by the boundary layer shock wave interaction. The classification of elementary structures will be presented. In addition, the possible occurrence of bifurcation will also be studied. The second Chapter will be devoted to studying specific cases of transonic turbulent flow. The analysis of numerical results will be bounded to the shock wave structure. Studies shall include: the influence of the numerical scheme, three-dimensional effects connected with the changing width of the channel, a comparison to experiment and the influence of the symmetric boundary condition on the flow prediction in the channel. Finally, the boundary layer influence on the 1-foot structure will also be presented. Chapter three will present the separation structures. Here too a comparison to experiments will be done. Changes in separation structures connected with the width of the channel will be studied. The influence of the symmetry boundary condition will be shown. Finally, the specification of the basic flow structures will be done.
    Źródło:
    TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 1999, 3, 1; 53-140
    1428-6394
    Pojawia się w:
    TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Interactions of retigabine with topiramate in the mouse tonic-clonic seizure model and chimney test - an isobolographic analysis
    Autorzy:
    Zagaja, Mirosław
    Miziak, Barbara
    Kondrat-Wróbel, Maria W.
    Andres-Mach, Marta
    Wróblewska-Łuczka, Paula
    Adamczuk, Piotr
    Chmura, Robert
    Czuczwar, Stanisław Jerzy
    Łuszczki, Jarogniew J.
    Powiązania:
    https://bibliotekanauki.pl/articles/972722.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Medycyny Wsi
    Tematy:
    maximal electro-shock
    drug interaction
    isobolographic analysis
    Retigabine
    Topiramate
    Opis:
    Introduction and objectives. Nowadays, one of the treatment options for patients with refractory epilepsy is polytherapy with two or more antiepileptic drugs (AEDs). Retigabine (RTG) is a novel third-generation AED with unique molecular mechanisms of action that has recently been approved as an add-on drug for the treatment of tonic-clonic seizures. To characterize types of interactions between RTG and topiramate (TPM – a second-generation AED), the maximal electroshock- induced seizure model (MES) and chimney test in mice were used. Materials and method. In the MES model, the anticonvulsant effects of the drugs in terms of suppression of tonic-clonic seizures in male albino Swiss mice were assessed. In the chimney test, the acute neurotoxic effects of the drugs with respect to impairment of motor coordination were determined. Type I isobolographic analysis for the combination of RTG and TPM was applied to assess the anticonvulsant and neurotoxic effects in both the MES and chimney tests. Total brain concentrations of RTG and TPM were measured to exclude any pharmacokinetic interaction between drugs. Results. The type I isobolographic analysis of interaction revealed that the combination of RTG with TPM produced additive interaction in the MES test and additivity, with a slight tendency towards antagonism in terms of acute neurotoxic effects in the chimney test. Neither RTG nor TPM mutually affected total brain concentrations in the experimental animals. Conclusions. The isobolographically analyzed combination of RTG with TPM is favourable and may be recommended to some patients with refractory epilepsy.
    Źródło:
    Journal of Pre-Clinical and Clinical Research; 2017, 11, 1; 61-65
    1898-2395
    Pojawia się w:
    Journal of Pre-Clinical and Clinical Research
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Identification of the boundary layer shock wave interaction type in transonic flow regime
    Autorzy:
    Placek, R.
    Stryczniewicz, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/242396.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    transonic flow
    wind tunnel techniques
    shock wave
    airfoil
    boundary layer interaction
    Opis:
    The paper presents various approaches to wind tunnel data analysis when identifying the shock wave boundary layer interaction type. The investigation was carried out in the transonic flow regime in the N-3 Wind Tunnel of Institute of Aviation. The Mach number was 0.7 and Reynolds number was approximate equal 2.85 million. The object of the research was a laminar airfoil in configuration without and with turbuliser device mounted on the upper model surface. In order to achieve turbulent boundary layer in front of the shock wave the carborundum strip was used. The effect of the varying angle of incidence on the flow filed was investigated. During experimental research, different means and test methods were applied (pressure measurements, Schlieren and oil visualisation, Particle Image Velocimetry (PIV), hot-film anemometry). The results were analysed in terms of the shock wave boundary interaction type. Most of results were in good agreement with theoretical models reported in the literature. The study showed that combination of various measurement techniques should be used in the shock wave boundary investigations in order to achieve more consistent and reliable conclusions. The results of the presented research can also be used for better understanding other mechanisms i.e. the boundary layer shock wave separation process in transonic flow regime.
    Źródło:
    Journal of KONES; 2016, 23, 2; 285-292
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Modelling the shock absorber piston valve using 2-way fluid-structure interaction
    Autorzy:
    Buczkowski, Daniel
    Nowak, Grzegorz
    Powiązania:
    https://bibliotekanauki.pl/articles/2098174.pdf
    Data publikacji:
    2021
    Wydawca:
    Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
    Tematy:
    shock absorber
    fluid-structure interaction
    CFD
    damping forces
    piston valve
    amortyzator
    oddziaływanie płyn-struktura
    siły tłumiące
    suwak tłoczkowy
    Opis:
    The aim of this study is to examine the strongly coupled Fluid-Structure Interaction approach as a comprehensive method of predicting the performance of the shock absorber piston valve. For this purpose, numerical simulation sand experimental testing are carried out. The coupled CFD-FEA numerical model described in this article, contrary to the attempts made so far, takes into account the influence of contact between valve discs and the initial conditions of the disc stack preload. The model is based on the actual valve geometry used in the shock absorber design. As a result, the described approach is intended for use in industrial applications in development works, in particular, at the conceptual stage. To prove the reliability of the model, two valve compositions are chosen to be measured on a test bench and modelled in FSI simulations. For both of them, a satisfactory level of correlation is achieved, with the correlation error below 10% and well-predicted valve opening points. As a result, it is proved that the 2-way FSI approach has great potential to be successfully used to investigate the damper valve operation.
    Źródło:
    Transport Problems; 2021, 16, 4; 45--57
    1896-0596
    2300-861X
    Pojawia się w:
    Transport Problems
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Transonic flows, shock wave-turbulent boundary layer interaction
    Autorzy:
    Doerffer, P.
    Kaczyński, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/1953982.pdf
    Data publikacji:
    1998
    Wydawca:
    Politechnika Gdańska
    Tematy:
    transonic flows
    shock waves
    turbulent boundary layer interaction
    computational fluid dynamics CFD
    CFD
    flow configurations
    profile flow
    helicopter rotor
    hovering
    forward flight
    internal flows
    Opis:
    Shock wave-boundary layer interaction is one of the most important phenomenon in transonic flows. Due to its complexity it is difficult as well for experimental as for numerical study. The growing potential of CFD is therefore of great importance. Different aspects of shock wave-boundary layer interaction should be studied in different flow configurations. Therefore results concerning profile flow, helicopter rotor at hovering and forward flight and internal flows are presented in this paper. These are to illustrate our ability in CFD in general. Besides flow simulation the development of codes is carried out.
    Źródło:
    TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 1998, 2, 2; 271-286
    1428-6394
    Pojawia się w:
    TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-6 z 6

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