Thematische Bibliographien / Unsteady simulation

Inhaltsverzeichnis

  1. Zeitschriftenartikel
  2. Dissertationen
  3. Bücher
  4. Buchteile
  5. Konferenzberichte
  6. Berichte der Organisationen

Auswahl der wissenschaftlichen Literatur zum Thema „Unsteady simulation“

Autor: Grafiati
Veröffentlicht am 28. Juni 2021
Zuletzt aktualisiert am 17. Februar 2022

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Zeitschriftenartikel zum Thema "Unsteady simulation"

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Wang, Zhi Gang, und Zhen Ning Zhang. „Modeling and Simulation of Unsteady Aerodynamics on a Morphing Wing“. Applied Mechanics and Materials 427-429 (September 2013): 77–80. http://dx.doi.org/10.4028/www.scientific.net/amm.427-429.77.

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Modeling and simulation method of unsteady aerodynamics on morphing wings were investigated. The Unsteady Vortex Lattice Method is employed to model the unsteady aerodynamics of 3-D potential flow field surrounding the wing. An UVLM computer code was then developed and validated for numerical simulation. A morphing wing which changes its dihedral angle with constant angular velocity was investigated by the code, and the lift, induced drag, and pitching moment coefficients time histories were obtained. The results show that the UVLM code is an effective tool for simulations of unsteady aerodynamics on morphing wings.
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Torner, Benjamin, Lucas Konnigk, Sebastian Hallier, Jitendra Kumar, Matthias Witte und Frank-Hendrik Wurm. „Large eddy simulation in a rotary blood pump: Viscous shear stress computation and comparison with unsteady Reynolds-averaged Navier–Stokes simulation“. International Journal of Artificial Organs 41, Nr. 11 (13.06.2018): 752–63. http://dx.doi.org/10.1177/0391398818777697.

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Purpose: Numerical flow analysis (computational fluid dynamics) in combination with the prediction of blood damage is an important procedure to investigate the hemocompatibility of a blood pump, since blood trauma due to shear stresses remains a problem in these devices. Today, the numerical damage prediction is conducted using unsteady Reynolds-averaged Navier–Stokes simulations. Investigations with large eddy simulations are rarely being performed for blood pumps. Hence, the aim of the study is to examine the viscous shear stresses of a large eddy simulation in a blood pump and compare the results with an unsteady Reynolds-averaged Navier–Stokes simulation. Methods: The simulations were carried out at two operation points of a blood pump. The flow was simulated on a 100M element mesh for the large eddy simulation and a 20M element mesh for the unsteady Reynolds-averaged Navier-Stokes simulation. As a first step, the large eddy simulation was verified by analyzing internal dissipative losses within the pump. Then, the pump characteristics and mean and turbulent viscous shear stresses were compared between the two simulation methods. Results: The verification showed that the large eddy simulation is able to reproduce the significant portion of dissipative losses, which is a global indication that the equivalent viscous shear stresses are adequately resolved. The comparison with the unsteady Reynolds-averaged Navier–Stokes simulation revealed that the hydraulic parameters were in agreement, but differences for the shear stresses were found. Conclusion: The results show the potential of the large eddy simulation as a high-quality comparative case to check the suitability of a chosen Reynolds-averaged Navier–Stokes setup and turbulence model. Furthermore, the results lead to suggest that large eddy simulations are superior to unsteady Reynolds-averaged Navier–Stokes simulations when instantaneous stresses are applied for the blood damage prediction.
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Wang, Ziwei, Xiong Jiang, Ti Chen, Yan Hao und Min Qiu. „Numerical simulation of transonic compressor under circumferential inlet distortion and rotor/stator interference using harmonic balance method“. Modern Physics Letters B 32, Nr. 12n13 (10.05.2018): 1840021. http://dx.doi.org/10.1142/s0217984918400213.

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Simulating the unsteady flow of compressor under circumferential inlet distortion and rotor/stator interference would need full-annulus grid with a dual time method. This process is time consuming and needs a large amount of computational resources. Harmonic balance method simulates the unsteady flow in compressor on single passage grid with a series of steady simulations. This will largely increase the computational efficiency in comparison with the dual time method. However, most simulations with harmonic balance method are conducted on the flow under either circumferential inlet distortion or rotor/stator interference. Based on an in-house CFD code, the harmonic balance method is applied in the simulation of flow in the NASA Stage 35 under both circumferential inlet distortion and rotor/stator interference. As the unsteady flow is influenced by two different unsteady disturbances, it leads to the computational instability. The instability can be avoided by coupling the harmonic balance method with an optimizing algorithm. The computational result of harmonic balance method is compared with the result of full-annulus simulation. It denotes that, the harmonic balance method simulates the flow under circumferential inlet distortion and rotor/stator interference as precise as the full-annulus simulation with a speed-up of about 8 times.
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Adamczyk, J. J., M. L. Celestina und Jen Ping Chen. „Wake-Induced Unsteady Flows: Their Impact on Rotor Performance and Wake Rectification“. Journal of Turbomachinery 118, Nr. 1 (01.01.1996): 88–95. http://dx.doi.org/10.1115/1.2836611.

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The impact of wake-induced unsteady flows on blade row performance and the wake rectification process is examined by means of numerical simulation. The passage of a stator wake through a downstream rotor is first simulated using a three-dimensional unsteady viscous flow code. The results from this simulation are used to define two steady-state inlet conditions for a three-dimensional viscous flow simulation of a rotor operating in isolation. The results obtained from these numerical simulations are then compared to those obtained from the unsteady simulation both to quantify the impact of the wake-induced unsteady flow field on rotor performance and to identify the flow processes which impact wake rectification. Finally, the results from this comparison study are related to an existing model, which attempts to account for the impact of wake-induced unsteady flows on the performance of multistage turbomachinery.
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Sznajder, Janusz, und Jerzy Zółtak. „APPLICATION OF AN EULER SOLVER TO SELECTED PROBLEMS IN FLIGHT DYNAMICS“. Aviation 11, Nr. 2 (31.03.2007): 13–22. http://dx.doi.org/10.3846/16487788.2007.9635956.

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Several applications of a Euler solver with the formulation of the flow equations in the noninertial reference system with steady and unsteady flow analysis are presented. The steady‐flow applications include determination of aerodynamic derivatives with respect to angular velocity and analysis of vortical flow over a delta wing at high angles of attack with the determination of aerodynamic coefficients and analysis of vortex breakdown. The unsteady flow analysis is applied in the simulation of a rapid manoeuvre for the determination of unsteady forces. The results of this simulation are compared with results of simulations using steady‐flow approximation in order to assess the advantages of unsteady flow analysis in the simulation of aircraft manoeuvres.
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Feng, Guang, Wei-zheng Chen, Xue-sen Chu, Zhi Wang, Ming-hui Zhang und Wei-qi Chen. „Simulation of unsteady artificial supercavities“. Journal of Hydrodynamics 22, S1 (Oktober 2010): 862–68. http://dx.doi.org/10.1016/s1001-6058(10)60050-9.

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Hu, Le, Shu Jia Zhang und Cheng Xu. „The Use of Steady Multi-Phase Position and Unsteady Computational Methods in the Numerical Simulation of Double-Suction Centrifugal Pump“. Advanced Materials Research 181-182 (Januar 2011): 201–5. http://dx.doi.org/10.4028/www.scientific.net/amr.181-182.201.

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In order to compare the steady multi-phase and unsteady calculation in double-suction centrifugal pump application, this article simulates the internal turbulent flow of the 150S-50 double suction centrifugal pump. Numerical simulation uses realizable turbulence model, simulating with two methods of steady multi-phase and unsteady in 7 cases. Based on the numerical simulation, the head, shaft power, efficiency were calculated, the simulated performance curves of a double suction centrifugal pump is processed. The results show that: The results of unsteady simulation are closer with the experimental data.
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Münsterjohann, Sven, Jens Grabinger, Stefan Becker und Manfred Kaltenbacher. „CAA of an Air-Cooling System for Electronic Devices“. Advances in Acoustics and Vibration 2016 (20.10.2016): 1–17. http://dx.doi.org/10.1155/2016/4785389.

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This paper presents the workflow and the results of fluid dynamics and aeroacoustic simulations for an air-cooling system as used in electronic devices. The setup represents a generic electronic device with several electronic assemblies with forced convection cooling by two axial fans. The aeroacoustic performance is computed using a hybrid method. In a first step, two unsteady CFD simulations using the Unsteady Reynolds-Averaged Navier-Stokes simulation with Shear Stress Transport (URANS-SST) turbulence model and the Scale Adaptive Simulation with Shear Stress Transport (SAS-SST) models were performed. Based on the unsteady flow results, the acoustic source terms were calculated using Lighthill’s acoustic analogy. Propagation of the flow-induced sound was computed using the Finite Element Method. Finally, the results of the acoustic simulation are compared with measurements and show good agreement.
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Salehian, Saman, und Reda R. Mankbadi. „Simulations of rocket launch noise suppression with water injection from impingement pad“. International Journal of Aeroacoustics 19, Nr. 3-5 (Juni 2020): 207–39. http://dx.doi.org/10.1177/1475472x20930653.

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The focus of this work is on understanding the effect of water injection from the launch pad on the noise generated during rocket’s lift-off. To simplify the problem, we consider a supersonic jet impinging on a flat plate with water injection from the impingement plate. The Volume of Fluid model is adopted in this work to simulate the two-phase flow. A Hybrid Large Eddy Simulation – Unsteady Reynolds Averaged Simulation approach is employed to model turbulence, wherein Unsteady Reynolds Averaged Simulation is used near the walls, and Large Eddy Simulation is used elsewhere in the computational domain. The numerical issues associated with simulating the noise of two-phase supersonic flow are addressed. The pressure fluctuations on the impingement plate obtained from numerical simulations agree well with the experimental data. Furthermore, the predicted effect of water injection on the far-field broadband noise is consistent with that of the experiment. The possible mechanisms for noise reduction by water injection are discussed.
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Hassan, O., E. J. Probert, K. Morgan und N. P. Weatherill. „Unsteady flow simulation using unstructured meshes“. Computer Methods in Applied Mechanics and Engineering 189, Nr. 4 (September 2000): 1247–75. http://dx.doi.org/10.1016/s0045-7825(99)00376-x.

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Dissertationen zum Thema "Unsteady simulation"

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Smith, Thomas M. „Unsteady simulations of turbulent premixed reacting flows“. Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/13097.

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Stallard, Timothy J. „Simulation of unsteady viscous flow-structure interaction“. Thesis, University of Oxford, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.418130.

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The design of slender structures such as longspan bridges, masts, offshore risers and cables is strongly influenced by their response behaviour when subjected to unsteady loads due to wind, waves and current. Simulation of the behaviour of a viscous flow past a structural cross section is of great importance to engineers concerned with the design of such structures. Offshore engineers are concerned with estimating the magnitude of structural forces induced by the most severe storm-induced wave events. Numerous studies have been conducted in an effort to estimate the structural forces induced by both regular and irregular waves. However, estimation of the maximum extreme wave-induced structural forces, particularly for relatively small diameter horizontal components, has received less attention. Since the most widely used method for estimating the force experienced by a bluff body subjected to wave loading is the empirical drag-inertia equation developed by Morison, O’ Brien, Johnson, and Schaaf (1950), it is important to determine whether this equation is adequate to describe the forces imposed by extremely large ocean waves. A method is presented for the simulation of incompressible viscous flow past acylinder using a stream function vorticity-transport formulation discretised on a cutcell quadtree mesh. A cut-cell technique is employed to provide accurate boundary representation and to facilitate the simulation of flow past a moving boundary. The finite volume discretisation consists of second-order accurate central difference approximations within uncut flow cells and a polynomial reconstruction technique within the cut-cells that are intersected by the solid boundary. Several preliminary validation tests concerned with flow past a circular cylinder are presented to confirm the accuracy of the numerical model. Firstly, the cut-cell discretisation is applied to the solution of the Euler equations and is shown to be almost second order accurate. Comparisons of wake geometry and force coefficients for steady and oscillatory flows at low Reynolds number are then made with existing results, and show satisfactory agreement. Preliminary tests are presented to assess the accuracy of a cut-cell based method for simulating flow past a circular body that moves across a background mesh. A series of experiments is also presented concerned with the measurement of theforce experienced by a circular cylinder undergoing a pre-defined two-dimensionalmotion within a still fluid. The cylinder trajectory is representative of the motionof a fluid particle beneath an idealised large ocean wave as defined by the NewWave formulation (Tromans et al. 1991). It is observed that, whilst the magnitude of high frequency vortex induced force fluctuations varies with the ratio of wave amplitude to cylinder diameter (A=D) and the wave spectrum shape, the overall shape of both x- and y-direction force time histories is very similar for all wave groups for which the underlying spectrum has the same shape. For all of the two-dimensional cylinder motions considered, the spectrum of both measured forces closely approximates the spectrum of uq (where u is a component of the velocity vector and q the absolute velocity) and, as a result, the vector form of the well known equation developed by Morison et al. (1950) is shown to provide a satisfactory estimate of the cartesian force components. The high frequency component of the force that is not captured by the Morison et al. equation is clearly identified as a lift-type force in the radial direction. For design purposes, a reasonable estimate of the magnitude of the peak force is obtained by neglecting inertial forces and employing a drag coefficient CD = 1.0.
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Taflin, David E. „Numerical simulation of unsteady hypersonic chemically reacting flow /“. Thesis, Connect to this title online; UW restricted, 1995. http://hdl.handle.net/1773/9967.

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Young, John Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. „Numerical simulation of the unsteady aerodynamics of flapping airfoils“. Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2005. http://handle.unsw.edu.au/1959.4/38656.

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There is currently a great deal of interest within the aviation community in the design of small, slow-flying but manoeuvrable uninhabited vehicles for reconnaissance, surveillance, and search and rescue operations in urban environments. Inspired by observation of birds, insects, fish and cetaceans, flapping wings are being actively studied in the hope that they may provide greater propulsive efficiencies than propellers and rotors at low Reynolds numbers for such Micro-Air Vehicles (MAVs). Researchers have posited the Strouhal number (combining flapping frequency, amplitude and forward speed) as the parameter controlling flapping wing aerodynamics in cruising flight, although there is conflicting evidence. This thesis explores the effect of flapping frequency and amplitude on forces and wake structures, as well as physical mechanisms leading to optimum propulsive efficiency. Two-dimensional rigid airfoils are considered at Reynolds number 2,000 ??? 40,000. A compressible Navier-Stokes simulation is combined with numerical and analytical potential flow techniques to isolate and evaluate the effect of viscosity, leading and trailing edge vortex separation, and wake vortex dynamics. The wake structures of a plunging airfoil are shown to be sensitive to the flapping frequency independent of the Strouhal number. For a given frequency, the wake of the airfoil exhibits ???vortex lock-in??? as the amplitude of motion is increased, in a manner analogous to an oscillating circular cylinder. This is caused by interaction between the flapping frequency and the ???bluff-body??? vortex shedding frequency apparent even for streamlined airfoils at low Reynolds number. The thrust and propulsive efficiency of a plunging airfoil are also shown to be sensitive to the flapping frequency independent of Strouhal number. This dependence is the result of vortex shedding from the leading edge, and an interaction between the flapping frequency and the time for vortex formation, separation and convection over the airfoil surface. The observed propulsive efficiency peak for a pitching and plunging airfoil is shown to be the result of leading edge vortex shedding at low flapping frequencies (low Strouhal numbers), and high power requirements at large flapping amplitudes (high Strouhal numbers). The efficiency peak is governed by flapping frequency and amplitude separately, rather than the Strouhal number directly.
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Sbardella, Luca. „Simulation of unsteady turbomachinery flows for forced response predictions“. Thesis, Imperial College London, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.341913.

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Mossi, Michele. „Simulation of benchmark and industrial unsteady compressible turbulent fluid flows /“. [S.l.] : [s.n.], 1999. http://library.epfl.ch/theses/?nr=1958.

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Davis, Mallory. „Numerical Simulation of Unsteady Hydrodynamics in the Lower Mississippi River“. ScholarWorks@UNO, 2010. http://scholarworks.uno.edu/td/1126.

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Alterations along the Mississippi River, such as dams and levees, have greatly reduced the amount of freshwater and sediment that reaches the Louisiana coastal area. Several freshwater and sediment diversions have been proposed to combat the associated land loss problem. To aid in this restoration effort a 1-D numerical model was calibrated, validated, and used to predict the response of the river to certain stimuli, such as proposed diversions, channel closures, channel modifications, and relative sea level rise. This study utilized HEC-RAS 4.0, a 1-D mobile-bed numerical model, which was calibrated using a discharge hydrograph at Tarbert Landing and a stage hydrograph at the Gulf of Mexico, to calculate the hydrodynamics of the river. The model showed that RSLR will decrease the capacity of the Lower Mississippi River to carry bed material. The stage at Carrollton Gage is not significantly impacted by large scale diversions
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Prendergast, John Michael. „Simulation of unsteady 2-D wind by a vortex method“. Thesis, University of Cambridge, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.612179.

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Longo, Joel Joseph. „Unsteady Turbomachinery Flow Simulation With Unstructured Grids Using ANSYS Fluent“. The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1376875053.

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Ruiz, Anthony. „Unsteady Numerical Simulations of Transcritical Turbulent Combustion in Liquid Rocket Engines“. Thesis, Toulouse, INPT, 2012. http://www.theses.fr/2012INPT0009/document.

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Ces cinquantes dernières années, la majorité des paramètres de conception des moteurs cryotechniques ont été ajustés en l'absence d'une compréhension détaillée des phénomènes de combustion, en raison des limites des diagnostiques expérimentaux et des capacités de calcul. L'objectif de cette thèse est de réaliser des simulations numériques instationnaires d'écoulements réactifs transcritiques de haute fidélité, pour permettre une meilleure compréhension de la dynamique de flamme dans les moteurs cryotechniques et finalement guider leur amélioration. Dans un premier temps, la thermodynamique gaz-réel et son impact sur les schémas numériques sont présentés. Comme la Simulation aux Grandes Echelles (SGE) comporte des équations filtrées, les effets de filtrages induits par la thermodynamique gaz-réel sont ensuite mis en évidence dans une configuration transcritique type et un opérateur de diffusion artificiel, spécifique au gaz réel, est proposé pour lisser les gradients transcritiques en SGE. Dans un deuxième temps, une étude fondamentale du mélange turbulent et de la combustion dans la zone proche-injecteur des moteurs cryotechniques est menée grâce à la Simulation Numérique Directe (SND). Dans le cas non-réactif, les lâchers tourbillonnaires dans le sillage de la lèvre de l’injecteur jouent un rôle majeur dans le mélange turbulent et provoquent la formation de structures en peigne déjà observées expérimentalement dans des conditions similaires. Dans le cas réactif, la flamme reste attachée à la lèvre de l'injecteur, sans extinction locale, et les structures en peigne disparaissent. La structure de flamme est analysée et différents modes de combustion sont identifiés. Enfin, une étude de flamme-jet transcritique H2/O2, accrochée à un injecteur coaxial avec et sans retrait interne, est menée. Les résultats numériques sont d'abord validés par des données expérimentales pour l'injecteur sans retrait. Ensuite, la configuration avec retrait est comparée à la solution de référence sans retrait et à des données experimentales pour observer les effets de ce paramètre de conception sur l'efficacité de combustion
In the past fifty years, most design parameters of the combustion chamber of Liquid Rocket Engines (LREs) have been adjusted without a detailed understanding of combustion phenomena, because of both limited experimental diagnostics and numerical capabilities. The objective of the present thesis work is to conduct high-fidelity unsteady numerical simulations of transcritical reacting flows, in order to improve the understanding of flame dynamics in LRE, and eventually provide guidelines for their improvement. First real-gas thermodynamics and its impact on numerical schemes are presented. As Large-Eddy Simulation (LES) involves filtered equations, the filtering effects induced by real-gas thermodynamics are then highlighted in a typical 1D transcritical configuration and a specific real-gas artificial dissipation is proposed to smooth transcritical density gradients in LES. Then, a Direct Numerical Simulation (DNS) study of turbulent mixing and combustion in the near-injector region of LREs is conducted. In the non-reacting case, vortex shedding in the wake of the lip of the injector is shown to play a major role in turbulent mixing, and induces the formation of finger-like structures as observed experimentally in similar operating conditions. In the reacting case, the flame is attached to the injector rim without local extinction and the finger-like structures disappear. The flame structure is analyzed and various combustion modes are identified. Finally, a LES study of a transcritical H2/O2 jet flame, issuing from a coaxial injector with and without inner recess, is conducted. Numerical results are first validated against experimental data for the injector without recess. Then, the recessed configuration is compared to the reference solution and to experimental results, to scrutinize the effects of this design parameter on combustion efficiency
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Bücher zum Thema "Unsteady simulation"

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Srivastava, Rakesh. Simulation of unsteady rotational flow over propfan configuration. [Washington, DC: National Aeronautics and Space Administration, 1990.

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Janus, J. Mark. Unsteady flowfield simulation of ducted prop-fan configurations. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

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Srivastava, Rakesh. Simulation of unsteady rotational flow over propfan configuration. [Washington, DC: National Aeronautics and Space Administration, 1990.

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Jacobs, Peter A. Numerical simulation of transient hypervelocity flow in an expansion tube. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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Jacobs, Peter A. Numerical simulation of transient hypervelocity flow in an expansion tube. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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Jacobs, Peter A. Numerical simulation of transient hypervelocity flow in an expansion tube. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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Lawrence, C. Unsteady cascade aerodynamic response using a multiphysics simulation code. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2000.

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Deville, Michel, Thien-Hiep Lê und Yves Morchoisne, Hrsg. Numerical Simulation of 3-D Incompressible Unsteady Viscous Laminar Flows. Wiesbaden: Vieweg+Teubner Verlag, 1992. http://dx.doi.org/10.1007/978-3-663-00221-5.

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Meakin, Robert L. Domain connectivity among systems of overset grids: Progress report for NASA grant 2-783 submitted to NASA Ames Research Center, Computational Technology Branch ... Vacaville, CA: OMI, 1993.

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Yungster, S. Simulation of unsteady hypersonic combustion around projectiles in an expansion tube. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Buchteile zum Thema "Unsteady simulation"

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Roos Launchbury, David. „Large Eddy Simulation“. In Unsteady Turbulent Flow Modelling and Applications, 3–5. Wiesbaden: Springer Fachmedien Wiesbaden, 2016. http://dx.doi.org/10.1007/978-3-658-11912-6_2.

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Martelli, Francesco, Elisabetta Belardini und Paolo Adami. „Unsteady Flow Simulation of Turbine Stage“. In Computational Fluid Dynamics 2002, 667–72. Berlin, Heidelberg: Springer Berlin Heidelberg, 2003. http://dx.doi.org/10.1007/978-3-642-59334-5_101.

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Benbouta, Najat, Pascal Ferrand und Francis Leboeuf. „Simulation of 3D-Unsteady Internal Flows“. In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 91–106. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_5.

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Singh, Mritunjay Kumar, und Priyanka Kumari. „Contaminant Concentration Prediction Along Unsteady Groundwater Flow“. In Simulation Foundations, Methods and Applications, 257–75. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-05657-9_12.

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Lee, Chun-Hian, Yan-Qiu Chen und Ning Zhou. „Finite Element Simulation of Unsteady Separated Flows“. In Separated Flows and Jets, 143–48. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84447-8_19.

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Kiris, Cetin C., Dochan Kwak, William Chan und Jeffrey A. Housman. „Unsteady Flow Simulation of High Speed Turbopumps“. In Computational Fluid Dynamics 2006, 777–82. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-92779-2_122.

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Wächter, M., und G. Sachs. „Unsteady Heat Load Simulation for Hypersonic Cruise Optimization“. In Lecture Notes in Computational Science and Engineering, 325–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-642-55919-8_36.

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Chetverushkin, Boris N., und Eugene V. Shilnikov. „Unsteady Viscous Flow Simulation Based on QGD System“. In Mathematical Models of Non-Linear Excitations, Transfer, Dynamics, and Control in Condensed Systems and Other Media, 137–46. Boston, MA: Springer US, 1999. http://dx.doi.org/10.1007/978-1-4615-4799-0_11.

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9

Shilnikov, Eugene V. „Parallel Program Complex for 3D Unsteady Flow Simulation“. In Applied Parallel Computing. State of the Art in Scientific Computing, 722–31. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75755-9_88.

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10

Ducros, F., T. Soulères, F. Laporte, P. Moinat, C. Weber, V. Guinot und B. Caruelle. „High-Order Skew-Symmetric Jameson Schemes for Unsteady Compressible Flows“. In Direct and Large-Eddy Simulation III, 417–28. Dordrecht: Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-015-9285-7_35.

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Konferenzberichte zum Thema "Unsteady simulation"

1

Madden, T. J., und J. H. Miller. „Unsteady gas laser simulation“. In Proceedings. Users Group Conference. IEEE, 2004. http://dx.doi.org/10.1109/dod_ugc.2004.53.

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2

HU, CHIEN-CHUNG, C. LAN und JAY BRANDON. „Unsteady aerodynamic models for maneuvering aircraft“. In Flight Simulation and Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3626.

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Yao, Weigang. „Unsteady Aerodynamic Force Modeling via POD“. In AIAA Modeling and Simulation Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5685.

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Ananthan, Shreyas, James Baeder, Jayanarayanan Sitaraman, Seonghyeon Hahn und Gianluca Iaccarino. „Hybrid Unsteady Simulation of Helicopters: HUSH“. In 26th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-7339.

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Bond, Derek, und Hamid Johari. „Numerical Simulation of Unsteady Axisymmetric Jets“. In 3rd Theoretical Fluid Mechanics Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3081.

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Kuwahara, Kunio. „Unsteady flow simulation and its visualization“. In 30th Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3405.

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Adolfo, Dominique, und Carlo Carcasci. „Unsteady simulation of natural gas networks“. In SECOND INTERNATIONAL CONFERENCE ON MATERIAL SCIENCE, SMART STRUCTURES AND APPLICATIONS: ICMSS-2019. AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5138734.

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Tang, Jing. „Numerical simulation of unsteady ship airwakes“. In 2017 7th International Conference on Advanced Design and Manufacturing Engineering (ICADME 2017). Paris, France: Atlantis Press, 2017. http://dx.doi.org/10.2991/icadme-17.2017.3.

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Greber, Isaac. „Molecular dynamics simulation of unsteady diffusion“. In RAREFIED GAS DYNAMICS: 22nd International Symposium. AIP, 2001. http://dx.doi.org/10.1063/1.1407588.

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ATWOOD, CHRISTOPHER. „An upwind approach to unsteady flowfield simulation“. In Flight Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3100.

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Berichte der Organisationen zum Thema "Unsteady simulation"

1

Tsynkov, S. V. Artificial Boundary Conditions for the Numerical Simulation of Unsteady Electromagnetic Waves. Fort Belvoir, VA: Defense Technical Information Center, Januar 2003. http://dx.doi.org/10.21236/ada454447.

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Marcum, David L. Computational Simulation of Unsteady, Viscous, Hypersonic Flow about Flight Vehicles with Store Separation. Fort Belvoir, VA: Defense Technical Information Center, Februar 2001. http://dx.doi.org/10.21236/ada387492.

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3

You, Donghyun, William Bromby und Adamandios Sifounakis. Large-Eddy Simulation Analysis of Unsteady Separation Over a Pitching Airfoil at High Reynolds Number. Fort Belvoir, VA: Defense Technical Information Center, Dezember 2013. http://dx.doi.org/10.21236/ada608653.

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4

Jameson, Antony, und Peter E. Vincent. High-Order Numerical Algorithms for Steady and Unsteady Simulation of Viscous Compressible Flow with Shocks. Fort Belvoir, VA: Defense Technical Information Center, Juni 2010. http://dx.doi.org/10.21236/ada563587.

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Kokes, Joseph, Mark Costello und Jubaraj Sahu. Generating an Aerodynamic Model for Projectile Flight Simulation Using Unsteady, Time Accurate Computational Fluid Dynamic Results. Fort Belvoir, VA: Defense Technical Information Center, September 2006. http://dx.doi.org/10.21236/ada457421.

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6

Duque, Earl, Steve Legensky, Brad Whitlock, David Rogers, Andrew Bauer, Scott Imlay, David Thompson und Seiji Tsutsumi. Summary of the SciTech 2020 Technical Panel on In Situ/In Transit Computational Environments for Visualization and Data Analysis. Engineer Research and Development Center (U.S.), Juni 2021. http://dx.doi.org/10.21079/11681/40887.

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Annotation:
At the AIAA SciTech 2020 conference, the Meshing, Visualization and Computational Environments Technical Committee hosted a special technical panel on In Situ/In Transit Computational Environments for Visualization and Data Analytics. The panel brought together leading experts from industry, software vendors, Department of Energy, Department of Defense and the Japan Aerospace Exploration Agency (JAXA). In situ and in transit methodologies enable Computational Fluid Dynamic (CFD) simulations to avoid the excessive overhead associated with data I/O at large scales especially as simulations scale to millions of processors. These methods either share the data analysis/visualization pipelines with the memory space of the solver or efficiently off load the workload to alternate processors. Using these methods, simulations can scale and have the promise of enabling the community to satisfy the Knowledge Extraction milestones as envisioned by the CFD Vision 2030 study for "on demand analysis/visualization of a 100 Billion point unsteady CFD simulation". This paper summarizes the presentations providing a discussion point of how the community can achieve the goals set forth in the CFD Vision 2030.
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Rahai, Hamid, und Assma Begum. Numerical Investigations of Transient Wind Shear from Passing Vehicles Near a Road Structure (Part I: Unsteady Reynolds-Averaged Navier-Stokes Simulations). Mineta Transportation Institute, Januar 2021. http://dx.doi.org/10.31979/mti.2020.1933.

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In this research, the authors performed unsteady numerical simulations of a moving Ahmed body under a freeway overpass at different distances from the bridge columns in order to evaluate transient wind shear and the wind load on these columns. Results have shown that when the vehicle is at 0.75W distance from the bridge columns, an unsteady wind speed of up to 24 m/s is observed at the columns with a pressure coefficient difference of 0.9. Here W is the width of the vehicle. These results indicate with an appropriate system for harnessing these wind energy potentials, significant renewable electric power could be generated with zero carbon footprint.
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Edoh, Ayaboe, Ann Karagozian, Charles Merkle und Venkateswaran Sankaran. Investigation of Optimal Numerical Methods for High Reynolds Number Unsteady Simulations (Briefing Charts). Fort Belvoir, VA: Defense Technical Information Center, April 2014. http://dx.doi.org/10.21236/ada614100.

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9

Harmon, C. B., und William Dieterich. A 3-Degree-of-Freedom Flight Simulator Evaluation of Unsteady Aerodynamics Effects. Fort Belvoir, VA: Defense Technical Information Center, August 1991. http://dx.doi.org/10.21236/ada241540.

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Sahu, Jubaraj, Frank Fresconi und Karen R. Heavey. Unsteady Aerodynamic Simulations of a Finned Projectile at a Supersonic Speed With Jet Interaction. Fort Belvoir, VA: Defense Technical Information Center, Juni 2014. http://dx.doi.org/10.21236/ada606268.

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