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Literatura académica sobre el tema "Unsteady computations"

Autor: Grafiati

Publicado: 10 de marzo de 2023

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Artículos de revistas sobre el tema "Unsteady computations"

Ramamurti, Ravi, William C. Sandberg, Rainald Löhner, Jeffrey A. Walker y Mark W. Westneat. "Fluid dynamics of flapping aquatic flight in the bird wrasse:three-dimensional unsteady computations with fin deformation". Journal of Experimental Biology 205, n.º 19 (1 de octubre de 2002): 2997–3008. http://dx.doi.org/10.1242/jeb.205.19.2997.

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SUMMARY Many fishes that swim with the paired pectoral fins use fin-stroke parameters that produce thrust force from lift in a mechanism of underwater flight. These locomotor mechanisms are of interest to behavioral biologists,biomechanics researchers and engineers. In the present study, we performed the first three-dimensional unsteady computations of fish swimming with oscillating and deforming fins. The objective of these computations was to investigate the fluid dynamics of force production associated with the flapping aquatic flight of the bird wrasse Gomphosus varius. For this computational work, we used the geometry of the wrasse and its pectoral fin,and previously measured fin kinematics, as the starting points for computational investigation of three-dimensional (3-D) unsteady fluid dynamics. We performed a 3-D steady computation and a complete set of 3-D quasisteady computations for a range of pectoral fin positions and surface velocities. An unstructured, grid-based, unsteady Navier—Stokes solver with automatic adaptive remeshing was then used to compute the unsteady flow about the wrasse through several complete cycles of pectoral fin oscillation. The shape deformation of the pectoral fin throughout the oscillation was taken from the experimental kinematics. The pressure distribution on the body of the bird wrasse and its pectoral fins was computed and integrated to give body and fin forces which were decomposed into lift and thrust. The velocity field variation on the surface of the wrasse body, on the pectoral fins and in the near-wake was computed throughout the swimming cycle. We compared our computational results for the steady, quasi-steady and unsteady cases with the experimental data on axial and vertical acceleration obtained from the pectoral fin kinematics experiments. These comparisons show that steady state computations are incapable of describing the fluid dynamics of flapping fins. Quasi-steady state computations, with correct incorporation of the experimental kinematics, are useful when determining trends in force production, but do not provide accurate estimates of the magnitudes of the forces produced. By contrast, unsteady computations about the deforming pectoral fins using experimentally measured fin kinematics were found to give excellent agreement, both in the time history of force production throughout the flapping strokes and in the magnitudes of the generated forces.

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Allen, C. B. "Grid adaptation for unsteady flow computations". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, n.º 4 (1 de abril de 1997): 237–50. http://dx.doi.org/10.1243/0954410971532640.

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A grid adaptation procedure suitable for use during unsteady flow computations is described. Transfinite interpolation is used to generate structured grids for the computation of steady and unsteady Euler flows past aerofoils. This technique is well suited to unsteady flows, since instantaneous grid positions and speeds required by the flow solver are available directly from the algebraic mapping. A different approach to grid adaptation is described, wherein adaptation is performed by redistributing the interpolation parameters, instead of the physical grid positions. This results in the adapted grid positions, and hence speeds, still being available algebraically. Grid adaptation during an unsteady computation is performed continuously by imposing an ‘adaptation velocity’ on grid points, thereby applying the adaptation over several time steps and avoiding the interpolation of the solution from one grid to another, which is associated with instantaneous adaptation. For both steady and unsteady flows the adapted grid technique is shown to produce sharper shock resolution for a very small increase in CPU (central processing unit) requirements.

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Wechsler, K., M. Breuer y F. Durst. "Steady and Unsteady Computations of Turbulent Flows Induced by a 4/45° Pitched-Blade Impeller". Journal of Fluids Engineering 121, n.º 2 (1 de junio de 1999): 318–29. http://dx.doi.org/10.1115/1.2822210.

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The present paper summarizes steady and unsteady computations of turbulent flow induced by a pitched-blade turbine (four blades, 45° inclined) in a baffled stirred tank. Mean flow and turbulence characteristics were determined by solving the Reynolds averaged Navier-Stokes equations together with a standard k-ε turbulence model. The round vessel had a diameter of T = 152 mm. The turbine of diameter T/3 was located at a clearance of T/3. The Reynolds number (Re) of the experimental investigation was 7280, and computations were performed at Re = 7280 and Re = 29,000. Techniques of high-performance computing were applied to permit grid sensitivity studies in order to isolate errors resulting from deficiencies of the turbulence model and those resulting from insufficient grid resolution. Both steady and unsteady computations were performed and compared with respect to quality and computational effort. Unsteady computations considered the time-dependent geometry which is caused by the rotation of the impeller within the baffled stirred tank reactor. Steady-state computations also considered neglect the relative motion of impeller and baffles. By solving the governing equations of motion in a rotating frame of reference for the region attached to the impeller, the steady-state approach is able to capture trailing vortices. It is shown that this steady-state computational approach yields numerical results which are in excellent agreement with fully unsteady computations at a fraction of the time and expense for the stirred vessel configuration under consideration.

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Huo, Chao, Peng Lv y Anbang Sun. "Computational study on the aerodynamics of a long-shrouded contra-rotating rotor in hover". International Journal of Micro Air Vehicles 11 (enero de 2019): 175682931983368. http://dx.doi.org/10.1177/1756829319833686.

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This paper aims to investigate the aerodynamics including the global performance and flow characteristics of a long-shrouded contra-rotating rotor by developing a full 3D RANS computation. Through validations by current experiments on the same shrouded contra-rotating rotor, the computation using sliding mesh method and the computational zone with an extended nozzle downstream flow field effectively works; the time-averaged solution of the unsteady computation reveals that more uniform flow presents after the downstream rotor, which implies that the rear rotor rotating at opposite direction greatly compensates and reduces the wake; the unsteady computations further explore the flow field throughout the whole system, along the span and around blade tips. Complex flow patterns including the vortices and their interactions are indicated around the blade roots and tips. For further identifying rotor configurations, the rotor–rotor distance and switching two rotor speeds were studied. The computation reveals that setting the second rotor backwards decreases the wake scale but increases its intensity in the downstream nozzle zone. However, for the effect of switching speeds, computations cannot precisely solve the flow when the rear rotor under the windmill because of the upstream rotor rotating much faster than the other one. All the phenomena from computations well implement the experimental observations.

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Johansen, Stein T., Jiongyang Wu y Wei Shyy. "Filter-based unsteady RANS computations". International Journal of Heat and Fluid Flow 25, n.º 1 (febrero de 2004): 10–21. http://dx.doi.org/10.1016/j.ijheatfluidflow.2003.10.005.

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Adami, P. y F. Martelli. "Three-dimensional unsteady investigation of HP turbine stages". Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 220, n.º 2 (1 de marzo de 2006): 155–67. http://dx.doi.org/10.1243/095765005x69189.

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This article deals with a three-dimensional unsteady numerical simulation of the unsteady rotor—stator interaction in a HP turbine stage. The numerical approach consists of a computational fluid dynamics (CFD) parallel code, based on an upwind total variation diminishing finite volume approach. The computation has been carried out using a sliding plane approach with hybrid unstructured meshes and a two-equation turbulent closure. The turbine rig under investigation is representative of the first stage of aeronautic gas turbine engines. A brief description of the cascade, the experimental setup, and the measuring technique is provided. Time accurate CFD computations of pressure fluctuations and Nusselt number are discussed against the experimental data.

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De´nos, R., T. Arts, G. Paniagua, V. Michelassi y F. Martelli. "Investigation of the Unsteady Rotor Aerodynamics in a Transonic Turbine Stage". Journal of Turbomachinery 123, n.º 1 (1 de febrero de 2000): 81–89. http://dx.doi.org/10.1115/1.1314607.

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The paper focuses on the unsteady pressure field measured around the rotor midspan profile of the VKI Brite transonic turbine stage. The understanding of the complex unsteady flow field is supported by a quasi-three-dimensional unsteady Navier–Stokes computation using a k-ω turbulence model and a modified version of the Abu-Ghannam and Shaw correlation for the onset of transition. The agreement between computational and experimental results is satisfactory. They both reveal the dominance of the vane shock in the interaction. For this reason, it is difficult to identify the influence of vane-wake ingestion in the rotor passage from the experimental data. However, the computations allow us to draw some useful conclusions in this respect. The effect of the variation of the rotational speed, the stator–rotor spacing, and the stator trailing edge coolant flow ejection is investigated and the unsteady blade force pattern is analyzed.

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Luo, Da Hai, Chao Yan, Wei Lin Zheng y Wu Yuan. "A New PANS Model for Unsteady Separated Flow Simulations". Applied Mechanics and Materials 721 (diciembre de 2014): 182–86. http://dx.doi.org/10.4028/www.scientific.net/amm.721.182.

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A new Partially Averaged Navier-Stokes (PANS) model is proposed with the aim of simulating unsteady separated flows at reasonable computational expense. The unresolved-to-total ratio of kinetic energy (fk) related to PANS method is taken as a spatially varying and dynamically updating parameter in the computations. Turbulent flow past a backward-facing step is chosen as a test case in an effort to evaluate the model performance. PANS computations are compared to the experimental data and the traditional Detached Eddy Simulations (DES), showing their excellent capability of resolving turbulent fluctuations. Boundary layer shielding technique is also introduced into the PANS approach and effectively improves the computational results.

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Chen, C. P. y M. J. Sheu. "Unsteady transonic computations on porous aerofoils". AIAA Journal 29, n.º 1 (enero de 1991): 148–50. http://dx.doi.org/10.2514/3.10557.

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Korakianitis, T., P. Papagiannidis y N. E. Vlachopoulos. "Unsteady Flow/Quasi-Steady Heat Transfer Computations on a Turbine Rotor and Comparison With Experiments". Journal of Turbomachinery 124, n.º 1 (1 de agosto de 2001): 152–59. http://dx.doi.org/10.1115/1.1405419.

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The unsteady flow in stator–rotor interactions affects the structural integrity, aerodynamic performance of the stages, and blade-surface heat transfer. Numerous viscous and inviscid computer programs are used for the prediction of unsteady flows in two-dimensional and three-dimensional stator–rotor interactions. The relative effects of the various components of flow unsteadiness on heat transfer are under investigation. In this paper it is shown that for subsonic cases, the reduced frequency parameter for boundary-layer calculations is about two orders of magnitude smaller than the reduced frequency parameter for the core flow. This means that for typical stator–rotor interactions, the unsteady flow terms are needed to resolve the location of disturbances in the core flow, but in many cases the instantaneous disturbances can be input in steady-flow boundary-layer computations to evaluate boundary-layer effects in a quasi-steady approximation. This hypothesis is tested by comparing computations with experimental data on a turbine rotor for which there are extensive experimental heat transfer data available in the open literature. An unsteady compressible inviscid two-dimensional computer program is used to predict the propagation of the upstream stator disturbances into the downstream rotor passages. The viscous wake (velocity defect) and potential flow (pressure fluctuation) perturbations from the upstream stator are modeled at the computational rotor–inlet boundary. The effects of these interactions on the unsteady rotor flow result in computed instantaneous velocity and pressure fields. The period of the rotor unsteadiness is one stator pitch. The instantaneous velocity fields on the rotor surfaces are input in a steady-flow differential boundary-layer program, which is used to compute the instantaneous heat transfer rate on the rotor blades. The results of these quasi-steady heat-transfer computations are compared with the results of unsteady heat transfer experiments and with the results of previous unsteady heat transfer computations. The unsteady flow fields explain the unsteady amplitudes and phases of the increases and decreases in instantaneous heat transfer rate. It is concluded that the present method is accurate for quantitative predictions of unsteady heat transfer in subsonic turbine flows.

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Tesis sobre el tema "Unsteady computations"

Hellström, Fredrik. "Numerical computations of the unsteady flow in turbochargers". Doctoral thesis, KTH, Strömningsfysik, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-12742.

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Turbocharging the internal combustion (IC) engine is a common technique to increase the power density. If turbocharging is used with the downsizing technique, the fuel consumption and pollution of green house gases can be decreased. In the turbocharger, the energy of the engine exhaust gas is extracted by expanding it through the turbine which drives the compressor by a shaft. If a turbocharged IC engine is compared with a natural aspirated engine, the turbocharged engine will be smaller, lighter and will also have a better efficiency, due to less pump losses, lower inertia of the system and less friction losses. To be able to further increase the efficiency of the IC engine, the understanding of the highly unsteady flow in turbochargers must be improved, which then can be used to increase the efficiency of the turbine and the compressor. The main objective with this thesis has been to enhance the understanding of the unsteady flow in turbocharger and to assess the sensitivity of inflow conditions on the turbocharger performance. The performance and the flow field in a radial turbocharger turbine working under both non-pulsatile and pulsatile flow conditions has been assessed by using Large Eddy Simulation (LES). To assess the effects of different operation conditions on the turbine performance, different cases have been considered with different perturbations and unsteadiness of the inflow conditions. Also different rotational speeds of the turbine wheel were considered. The results show that the turbine cannot be treated as being quasi-stationary; for example,the shaft power varies for different frequencies of the pulses for the same amplitude of mass flow. The results also show that perturbations and unsteadiness that are created in the geometry upstream of the turbine have substantial effects on the performance of the turbocharger. All this can be summarized as that perturbations and unsteadiness in the inflow conditions to the turbine affect the performance. The unsteady flow field in ported shroud compressor has also been assessed by using LES for two different operational points. For an operational point near surge, the flow field in the entire compressor stage is unsteady, where the driving mechanism is an unsteadiness created in the volute. For an operational point far away from surge, the flow field in the compressor is relatively much more steady as compared with the former case. Although the stable operational point exhibits back-flow from the ported shroud channels, which implies that the flow into the compressor wheel is disturbed due to the structures that are created in the shear layer between the bulk flow and the back-flow from the ported shroud channels.
QC20100622

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Wu, Jiongyang. "Filter-based modeling of unsteady turbulent cavitating flow computations". [Gainesville, Fla.] : University of Florida, 2005. http://purl.fcla.edu/fcla/etd/UFE0011587.

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Hellström, Fredrik. "Numerical computations of the unsteady flow in a radial turbine". Licentiate thesis, KTH, Mechanics, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4660.

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Non-pulsatile and pulsatile flow in bent pipes and radial turbine has been assessed with numerical simulations. The flow field in a single bent pipe has been computed with different turbulence modelling approaches. A comparison with measured data shows that Implicit Large Eddy Simulation (ILES) gives the best agreement in terms of mean flow quantities. All computations with the different turbulence models qualitatively capture the so called Dean vortices. The Dean vortices are a pair of counter-rotating vortices that are created in the bend, due to inertial effects in combination with a radial pressure gradient. The pulsatile flow in a double bent pipe has also been considered. In the first bend, the Dean vortices are formed and in the second bend a swirling motion is created, which will together with the Dean vortices create a complex flow field downstream of the second bend. The strength of these structures will vary with the amplitude of the axial flow. For pulsatile flow, a phase shift between the velocity and the pressure occurs and the phase shift is not constant during the pulse depending on the balance between the different terms in the Navier- Stokes equations.

The performance of a radial turbocharger turbine working under both non-pulsatile and pulsatile flow conditions has also been investigated by using ILES. To assess the effect of pulsatile inflow conditions on the turbine performance, three different cases have been considered with different frequencies and amplitude of the mass flow pulse and different rotational speeds of the turbine wheel. The results show that the turbine cannot be treated as being quasi-stationary; for example, the shaft power varies with varying frequency of the pulses for the same amplitude of mass flow. The pulsatile flow also implies that the incidence angle of the flow into the turbine wheel varies during the pulse. For the worst case, the relative incidence angle varies from approximately −80° to +60°. A phase shift between the pressure and the mass flow at the inlet and the shaft torque also occurs. This phase shift increases with increasing frequency, which affects the accuracy of the results from 1-D models based on turbine maps measured under non-pulsatile conditions.

For a turbocharger working under internal combustion engine conditions, the flow into the turbine is pulsatile and there are also unsteady secondary flow components, depending on the geometry of the exhaust manifold situated upstream of the turbine. Therefore, the effects of different perturbations at the inflow conditions on the turbine performance have been assessed. For the different cases both turbulent fluctuations and different secondary flow structures are added to the inlet velocity. The results show that a non-disturbed inlet flow gives the best performance, while an inflow condition with a certain large scale eddy in combination with turbulence has the largest negative effect on the shaft power output.

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De, Rango Stan. "Implicit Navier-Stokes computations of unsteady flows using subiteration methods". Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1996. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/MQ51537.pdf.

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Hellström, Fredrik. "Numerical computations of the unsteady flow in a radial turbine /". Stockholm : Mekanik, Kungliga Tekniska högskolan, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4660.

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Nöid, Lovisa. "CFD computations of hydropower plant intake flow using unsteady RANS". Thesis, KTH, Kraft- och värmeteknologi, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-161894.

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At the intake of hydropower plants, air-core vortex formation is known to cause severe damage. In order to study how to prevent and reduce the origin of the vortex, Vattenfall has built a scale model of the Akkats hydropower plant dam, where scale testing is possible. This thesis work consists of discerning whether Computational Fluid Dynamics (CFD) in terms of solving the Unsteady Reynolds Average Navier-Stokes equations (URANS) can be used as a complement to scale testing. For this work, the RNG k-epsilon turbulence model is chosen, and the flow field is solved with implicit time discretization using a pressure-based solver, for three different inlet flow conditions. Despite significant differences in the inflow of these three cases, the resulting flow fields are surprisingly similar. A main result is that no vortex is formed in any of the cases. The cause of this is discussed, but the number of possible answers is large. The main purpose of the report has therefore become to lay the foundation for further research. Amongst the top priorities in parameters to investigate lies the choice of turbulence model, the surface height, the pressure discretization scheme and to perform calculations on a more expensive mesh.
Virvlar som uppstår vid intaget i vattenkraftverk kan orsaka stora skador. För att kunna göra studier om hur man bäst motverkar virveln och förhindrar dess uppkomst, har Vattenfall AB byggt en småskalig modell av dammen vid Akkats vattenkraftverk. Det här arbetet behandlar frågeställningen huruvida Computational Fluid Dynamics (CFD) med lösning av ekvationerna för Unsteady Reynolds Average Navier-Stokes (URANS) kan användas som ett komplement till dessa modell-tester. I det här arbetet har turbulensmodellen RNG k−epsilon valts och flödesfältet löses för tre olika tillstånd för flödet vid inloppet, med hjälp av implicit tidsdiskretisering tillsammans med en tryckbaserad ekvationslösare. Trots betydande skillnader för inflödet för dessa tre fall är de resulterande flödesfälten överraskande lika. Ett huvudresultat är att ingen virvel formas för någon av dessa fall. Anledningen till detta har diskuterats, men antalet möjliga anledningar är många. Huvudsyftet med den här rapporten har därför blivit att lägga en grund för framtida efterforskningar på området. Några av de viktigaste parametrarna att undersöka är valet av turbulensmodell, höjden på vattenytan, tryckdiskretiserings-schema samt att genomföra beräkningar för en finare mesh.

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Reid, Terry Vincent. "A Computational Approach For Investigating Unsteady Turbine Heat Transfer Due To Shock Wave Impact". Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/25983.

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The effects of shock wave impact on unsteady turbine heat transfer are investigated. A numerical approach is developed to simulate the flow physics present in a previously performed unsteady wind tunnel experiment. The windtunnel experiment included unheated and heated flows over a cascade of highly loaded turbine blades. After the flow over the blades was established, a single shock with a pressure ratio of 1.1 was introduced into the wind tunnel test section. A single blade was equipped with pressure transducers and heat flux microsensors. As the shock wave strikes the blade, time resolved pressure, temperature, and heat transfer data were recorded.
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Price, Jennifer Lou. "Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps". NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010713-170959.

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Price, Jennifer Lou. Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps. (Under the direction of Dr. Ndaona Chokani)The effect of a Gurney flap on an unsteady airfoil flow is experimentally and computationally examined. In the experiment, the details of the unsteady boundary layer events on the forward portion of the airfoil are measured. In the computation, the features of the global unsteady flow are documented and correlated with the experimental observations.The experiments were conducted in the North Carolina State University subsonic wind tunnel on an oscillating airfoil at pitch rates of 65.45 degrees/sec and 130.9 degrees/sec. The airfoil has a NACA0012 cross-section and is equipped with a 1.5% or 2.5% chord Gurney flap. The airfoil is tested at Reynolds numbers of 96,000, 169,000 and 192,000 for attached and light dynamic stall conditions. An array of surface-mounted hot-film sensors on the forward 25% chord of the airfoil is used to measure the unsteady laminar boundary layer separation, transition-to-turbulence, and turbulent reattachment. In parallel with the experiments incompressible Navier-Stokes computations are conducted for the light dynamic stall conditions on the airfoil with a 2.5%c Gurney flap at a Reynolds number of 169,000.The experimental measurements show that the effect of the Gurney flap is to move the separation, transition and reattachment forward on the airfoil. This effect is more marked during the airfoil's pitch-down than during pitch-up. The computational results verify these observations, and also show that the shedding of the dynamic stall vortex is delayed. Thus the adverse effects of dynamic stall are mitigated by the Gurney flap.

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Bodin, Olle. "Numerical Computations of Internal Combustion Engine related Transonic and Unsteady Flows". Licentiate thesis, Stockholm : Mekanik, Kungliga Tekniska högskolan, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-9945.

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Novacek, Thomas Hans. "Computations of unsteady forces and moments for a transonic rotor with jet actuation". Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/50300.

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Libros sobre el tema "Unsteady computations"

Shankar, Vijaya. Unsteady full potential computations for complex configurations. New York: AIAA, 1987.

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United States. National Aeronautics and Space Administration., ed. Long time behavior of unsteady flow computations. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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Roe, P. L. Remote boundary conditions for unsteady multidimensional aerodynamic computations. Hampton, Va: ICASE, 1986.

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Roe, P. L. Remote boundary conditions for unsteady multidimensional aerodynamic computations. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

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Ide, Hiroshi. Unsteady full potential aeroelastic computations for flexible configurations. New York: AIAA, 1987.

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Rango, Stan De. Implicit navier-stokes computations of unsteady flows using subiteration methods. Ottawa: National Library of Canada, 1996.

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Center, Ames Research, ed. Computations of unsteady multistage compressor flows in a workstation environment. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.

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V, Kaza K. R. y United States. National Aeronautics and Space Administration., eds. A semianalytical technique for sensitivity analysis of unsteady aerodynamic computations. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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Rango, Stan De. Implicit navier-stokes computations of unsteady flows using subiteration methods. [Toronto]: Dept. of Aerospace Science and Engineering, University of Toronto, 1996.

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Nakamichi, Jiro. Some computations of unsteady Navier-Stokes flow around oscillating airfoil/wing. Tokyo: National Aerospace Laboratory, 1988.

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Capítulos de libros sobre el tema "Unsteady computations"

Hariharan, S. I. "Long Time Behavior of Unsteady Flow Computations". En Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 73–90. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_4.

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Bouwknegt, J. "Unsteady Flow Computations in Open Channel Hydraulics". En Hydraulic Design in Water Resources Engineering: Land Drainage, 353–62. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-662-22014-6_33.

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Hu, Hong y Li-Chuan Chu. "Unsteady Three-Dimensional Transonic Flow Computations Using Field Element Method". En Boundary Element Methods in Engineering, 140–46. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84238-2_19.

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Sahu, Jubaraj. "Numerical Computations of Unsteady Aerodynamics of Projectiles using an Unstructured Technique". En Computational Fluid Dynamics 2006, 886–93. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-92779-2_140.

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Shankar, V. y H. Ide. "Unsteady Aeroelastic Computations for Flexible Configurations at Transonic and Supersonic Speeds". En Symposium Transsonicum III, 465–78. Berlin, Heidelberg: Springer Berlin Heidelberg, 1989. http://dx.doi.org/10.1007/978-3-642-83584-1_37.

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Krishnamurthy, R., B. S. Sarma y S. M. Deshpande. "3-D KFMG Euler Computations for Unsteady Flows Around Oscillating Geometries". En Computational Fluid Dynamics 2002, 407–12. Berlin, Heidelberg: Springer Berlin Heidelberg, 2003. http://dx.doi.org/10.1007/978-3-642-59334-5_60.

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Maduta, R. y S. Jakirlic. "An Eddy-Resolving Reynolds Stress Transport Model for Unsteady Flow Computations". En Progress in Hybrid RANS-LES Modelling, 77–89. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-31818-4_6.

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Bramkamp, F. y J. Ballmann. "Implicit Euler Computations on Adaptive Meshes for Steady and Unsteady Transonic Flows". En IUTAM Symposium Transsonicum IV, 201–6. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-010-0017-8_31.

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Houwink, R. "Computations of Separated Subsonic and Transonic Flow about Airfoils in Unsteady Motion". En Numerical and Physical Aspects of Aerodynamic Flows III, 272–85. New York, NY: Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4926-9_16.

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Chang, Dongil y Stavros Tavoularis. "Parallel Computations of Unsteady Three-Dimensional Flows in a High Pressure Turbine". En High Performance Computing Systems and Applications, 20–29. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-12659-8_2.

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Actas de conferencias sobre el tema "Unsteady computations"

Djayapertapa, L. y C. Allen. "Aeroservoelastic computations in unsteady transonic flow". En 18th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4226.

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Ajmani, Kumud y Kuo-Huey Chen. "Unsteady-flow computations for the NCC". En 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-972.

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Gammacurta, Eric, Stéphane Etienne, Dominique Pelletier y André Garon. "Adaptive Remeshing for Unsteady RANS Computations". En 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-1070.

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Nunes, Ricardo, André Silva y Jorge Barata. "Unsteady Computations of a Ground Vortex". En 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-327.

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Mostafazadeh Davani, Bahareh, Ferran Marti, Behnam Pourghassemi, Feng Liu y Aparna Chandramowlishwaran. "Unsteady Navier-Stokes Computations on GPU Architectures". En 23rd AIAA Computational Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4508.

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Higuchi, H., F. Lu y Y. H. Chu. "Computations of unsteady two-dimensional vortex motions". En Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2379.

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Zhang, Sijun, Abraham Meganathan y Xiang Zhao. "Implicit Time Accurate Method for Unsteady Computations". En 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-166.

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van der Weide, Edwin, Georgi Kalitzin, Jorg Schluter y Juan Alonso. "Unsteady Turbomachinery Computations Using Massively Parallel Platforms". En 44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-421.

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SHANKAR, VIJAYA, HIROSHI IDE y THOMAS GOEBEL. "Unsteady full potential computations for complex configurations". En 25th AIAA Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-110.

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Alin, Niklas, Christer Fureby, S. Svennberg, William Sandberg, R. Ramamurti, N. Wikstrom, Rikard Bensow y Tobias Persson. "3D Unsteady Computations for Submarine-Like Bodies". En 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-1104.

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Informes sobre el tema "Unsteady computations"

Sahu, Jubaraj. Unsteady Flow Computations of a Finned Body in Supersonic Flight. Fort Belvoir, VA: Defense Technical Information Center, agosto de 2007. http://dx.doi.org/10.21236/ada471736.

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Bauer, Andrew y Berk Geveci. Computational Fluid Dynamics Co-processing for Unsteady Visualization. Fort Belvoir, VA: Defense Technical Information Center, septiembre de 2012. http://dx.doi.org/10.21236/ada570113.

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Polsky, Susan y Christopher Bruner. A Computational Study of Unsteady Ship Wake and Vortex Flows. Fort Belvoir, VA: Defense Technical Information Center, enero de 2000. http://dx.doi.org/10.21236/ada383641.

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McRae, D. S. y M. A. Zikry. Time Accurate Computation of Unsteady Shock Tunnel Flow with Coupled Diaphragm Ruptude Mechanics. Fort Belvoir, VA: Defense Technical Information Center, octubre de 1999. http://dx.doi.org/10.21236/ada378084.

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Duque, Earl, Steve Legensky, Brad Whitlock, David Rogers, Andrew Bauer, Scott Imlay, David Thompson y 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.), junio de 2021. http://dx.doi.org/10.21079/11681/40887.

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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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McRae, D. S. y Michael Neaves. Time Accurate Computation of Unsteady Hypersonic Inlet Flows with a Dynamic Flow Adaptive Mesh. Fort Belvoir, VA: Defense Technical Information Center, enero de 1998. http://dx.doi.org/10.21236/ada336232.

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Hinatsu, M. y Joel Ferziger. Numerical Computation of Unsteady Incompressible Flow in Complex Geometry Using a Composite Multigrid Technique. Fort Belvoir, VA: Defense Technical Information Center, agosto de 1991. http://dx.doi.org/10.21236/ada252075.

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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, febrero de 2001. http://dx.doi.org/10.21236/ada387492.

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Kokes, Joseph, Mark Costello y 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, septiembre de 2006. http://dx.doi.org/10.21236/ada457421.

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Wissink, Andrew, Jude Dylan, Buvana Jayaraman, Beatrice Roget, Vinod Lakshminarayan, Jayanarayanan Sitaraman, Andrew Bauer, James Forsythe, Robert Trigg y Nicholas Peters. New capabilities in CREATE™-AV Helios Version 11. Engineer Research and Development Center (U.S.), junio de 2021. http://dx.doi.org/10.21079/11681/40883.

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CREATE™-AV Helios is a high-fidelity coupled CFD/CSD infrastructure developed by the U.S. Dept. of Defense for aeromechanics predictions of rotorcraft. This paper discusses new capabilities added to Helios version 11.0. A new fast-running reduced order aerodynamics option called ROAM has been added to enable faster-turnaround analysis. ROAM is Cartesian-based, employing an actuator line model for the rotor and an immersed boundary model for the fuselage. No near-body grid generation is required and simulations are significantly faster through a combination of larger timesteps and reduced cost per step. ROAM calculations of the JVX tiltrotor configuration give a comparably accurate download prediction to traditional body-fitted calculations with Helios, at 50X less computational cost. The unsteady wake in ROAM is not as well resolved, but wake interactions may be a less critical issue for many design considerations. The second capability discussed is the addition of six-degree-of-freedom capability to model store separation. Helios calculations of a generic wing/store/pylon case with the new 6-DOF capability are found to match identically to calculations with CREATE™-AV Kestrel, a code which has been extensively validated for store separation calculations over the past decade.

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