Статті в журналах: "FLUENT SOLVER"

1

Pawłucki, Mateusz. "Multiple objective shape optimization in Ansys Fluent Solver." Mechanik, no. 11 (November 2015): 893–95. http://dx.doi.org/10.17814/mechanik.2015.11.587.

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2

Thwe, Kay, and Gao Gao. "An Evaluation of Model Ship Total Resistance by Measured and Different Methods." Applied Mechanics and Materials 110-116 (October 2011): 4433–38. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.4433.

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Prediction of total hull resistance has been investigated for many decades and it is still a challenging problem for naval architect. In this paper, the total resistance of round bilge monohull Model 100A is predicted by potential flow solver, Shipflow by Flowtech International AB, the commercial Reynold Average Navier Stroke (RANS) solver Fluent by Fluent, Inc., and analytical prediction by Slender Body Method (SBM). The total resistance was predicted by each code for the different model speeds (0.6m/s to 4.5m/s) and compared with experimental test data. The Fluent predictions were found to be in agreement with the experimental data in lower speed (0.6m/s to 2.5m/s). Shipflow results were more closed to experimental results than Fluent. Comparisons between the different solution methods were also discussed with the particular grid generation methods and numerical solution techniques. It is found that Slender Body Method can solve as easy and simple and it is effective to predict total resistance of thin ship monohull.

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3

Guo, Hao, Yimei Tian, Hailiang Shen, Yi Wang, and Mengxin Kang. "A landscape lake flow pattern design approach based on automated CFD simulation and parallel multiple objective optimization." Water Science and Technology 74, no. 5 (June 21, 2016): 1155–62. http://dx.doi.org/10.2166/wst.2016.308.

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A design approach for determining the optimal flow pattern in a landscape lake is proposed based on FLUENT simulation, multiple objective optimization, and parallel computing. This paper formulates the design into a multi-objective optimization problem, with lake circulation effects and operation cost as two objectives, and solves the optimization problem with non-dominated sorting genetic algorithm II. The lake flow pattern is modelled in FLUENT. The parallelization aims at multiple FLUENT instance runs, which is different from the FLUENT internal parallel solver. This approach: (1) proposes lake flow pattern metrics, i.e. weighted average water flow velocity, water volume percentage of low flow velocity, and variance of flow velocity, (2) defines user defined functions for boundary setting, objective and constraints calculation, and (3) parallels the execution of multiple FLUENT instances runs to significantly reduce the optimization wall-clock time. The proposed approach is demonstrated through a case study for Meijiang Lake in Tianjin, China.

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Aziz, M. S. Abdul, M. Z. Abdullah, C. Y. Khor, Z. M. Fairuz, A. M. Iqbal, M. Mazlan, and Mohd Sukhairi Mat Rasat. "Thermal Fluid-Structure Interaction in the Effects of Pin-Through-Hole Diameter during Wave Soldering." Advances in Mechanical Engineering 6 (January 1, 2014): 275735. http://dx.doi.org/10.1155/2014/275735.

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An effective simulation approach is introduced in this paper to study the thermal fluid-structure interaction (thermal FSI) on the effect of pin-through-hole (PTH) diameter on the wave soldering zone. A 3D single PTH connector and a printed circuit board model were constructed to investigate the capillary flow behavior when passing through molten solder (63SnPb37). In the analysis, the fluid solver FLUENT was used to solve and track the molten solder advancement using the volume of fluid technique. The structural solver ABAQUS was used to examine the von Mises stress and displacement of the PTH connector in the wave soldering process. Both solvers were coupled by MpCCI software. The effects of six different diameter ratios (0.1 < d/ D < 0.97) were studied through a simulation modeling. The use of ratio d/ D = 0.2 yielded a balanced filling profile and low thermal stress. Results revealed that filling level, temperature, and displacement exhibited polynomial behavior to d/ D. Stress of pin varied quadratically with the d/ D. The predicted molten solder profile was validated by experimental results. The simulation results are expected to provide better visualization and understanding of the wave soldering process by considering the aspects of thermal FSI.

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5

Kabdylkakov, Ye A., A. S. Suraev, and R. A. Irkimbekov. "APPLICATION OF THE TEXT INTERFACE OF THE ANSYS FLUENT PROGRAM FOR SIMULATION OF THE THERMOPHYSICAL STATE OF A TYPICAL EXPERIMENTAL DEVICE." NNC RK Bulletin, no. 3 (September 28, 2022): 55–63. http://dx.doi.org/10.52676/1729-7885-2022-3-55-63.

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The paper is dedicated to development of log of the ANSYS FLUENT program text commands. Although this program has well-developed and easy-to use graphical interface, command logs allow to conduct the configurations of the solver, optimizing the process of calculation justification safety of reactor experiments conducted at the “Institute of Atomic Energy” Branch of the RSE “National Nuclear Center of the Republic of Kazakhstan” (IAE Branch RSE NNC RK). Command logs allows to control the command to save the ANSYS FLUENT program solver as code in a separate file, which can later be used for other calculations. Command log allows to save settings the ANSYS FLUENT program solver as program code in a separate file, which can later be redacted and used for other calculations. Also, this would enable improving the group work of employees above one project, facilitate the exchange process of solver parameters and promptly make amendments and corrections. In the framework of this work, a technique for constructing a command log was developed for modeling thermophysical state of experimental devices in reactor experiments. The developed technique was tested on the example of solving a thermophysical task with a typical ED.

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6

Pajcin, Miroslav, Aleksandar Simonovic, Toni Ivanov, Dragan Komarov, and Slobodan Stupar. "Numerical analysis of a hypersonic turbulent and laminar flow using a commercial CFD solver." Thermal Science 21, suppl. 3 (2017): 795–807. http://dx.doi.org/10.2298/tsci160518198p.

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Computational fluid dynamics computations for two hypersonic flow cases using the commercial ANSYS FLUENT 16.2 CFD software were done. In this paper, an internal and external hypersonic flow cases were considered and analysis of the hypersonic flow using different turbulence viscosity models available in ANSYS FLUENT 16.2 as well as the laminar viscosity model were done. The obtained results were after compared and commented upon.

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7

Abdul Aziz, M. S., M. Z. Abdullah, and Kamarul Arifin Ahmad. "Numerical Investigations of Membrane Surface Effects on NACA 64₃- 218 Airfoil." Applied Mechanics and Materials 564 (June 2014): 60–65. http://dx.doi.org/10.4028/www.scientific.net/amm.564.60.

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This paper presents two dimensional fluid structure interaction (FSI) CFD analysis on the effect of skin thickness and Reynolds number on the aerodynamic performance of NACA 643-218 airfoil. Numerical investigations were performed using FLUENT 6.3 fluid flow solver and ABAQUS 6.8-1 structural solver. Coupling of both solvers in real time mode was accomplished with the Mesh based parallel Code Coupling Interface (MpCCI 3.1). The predicted and experimental results were found to be in excellent match. Generally, the results showed that the aerodynamic lift increases while drag decreases with the decrease of membrane thickness.

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8

Crha, Jakub, Pavlína Basařová, Marek C. Ruzicka, Ondřej Kašpar, and Maria Zednikova. "Comparison of Two Solvers for Simulation of Single Bubble Rising Dynamics: COMSOL vs. Fluent." Minerals 11, no. 5 (April 25, 2021): 452. http://dx.doi.org/10.3390/min11050452.

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Multiphase flows are a part of many industrial processes, where the bubble motion influences the hydrodynamic behavior of the batch. The current trend is to use numerical solvers that can simulate the movement and mutual interactions of bubbles. The aim of this work was to study how two commercial CFD solvers, COMSOL Multiphysics and Ansys Fluent, can simulate the motion of a single rising bubble in a stagnant liquid. Simulations were performed for spherical or slightly deformed bubbles (Db = 0.6, 0.8, and 1.5 mm) rising in water or in propanol. A simple 2D axisymmetric approach was used. Calculated bubble terminal velocities and bubble shape deformations were compared to both experimental data and theoretical estimations. Solver Comsol Multiphysics was able to precisely calculate the movement of smaller and larger bubbles; due to the 2D rotational symmetry, better results were obtained for small spherical bubbles. The deformation of larger bubbles was calculated sufficiently. Solver Ansys Fluent, in the setting used, failed to simulate the motion of small bubbles due to parasitic currents but allowed for modeling of the motion of larger bubbles. However, the description of the bubble velocity and shape was worse in comparison with experimental values.

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9

Ji, Hong, Wei Guo Zhu, Song Chen, and Jing Zhao. "Digital Analysis of Hydraulic Cone Valve Turbulence Based on Fluent 3D Solver." Applied Mechanics and Materials 385-386 (August 2013): 93–96. http://dx.doi.org/10.4028/www.scientific.net/amm.385-386.93.

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The hydraulic cone valve is an important basic component in Fluid drive and control technology. Characteristic of cone valve inner flow filed influences directly the valves performance. Especially when fluid flow in runner is turbulent, characteristics of flow field have great influence on the valves working performance.Main work of this paper is numerical calculation and simulation of cone valve inner runner flow field inside hydraulic hammer. First make a 3D modeling for cone valve using Pro/E, by fluent this paper analyses and discusses the distribution of hydraulic cone valve internal flow field including flow velocity field, pressure field and flow, etc when the cone valve core taper angle is 30°, the gap is 0.5 mm, and inlet velocity is different, analyses position and strength of the vortex, and finds out the main reason for energy consumption.The results of the study show that by the optimal design of the cone valve seat, the density degree of the flow and the size of the vortex is reduced, the energy loss is reduced, negative pressure zone also changes, the noise is reduced and the energy utilization is improved.

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10

Huang, Dennis, Zhigang Yang, and Randolph Chi Kin Leung. "Implementation of Direct Acoustic Simulation using ANSYS Fluent." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 5 (August 1, 2021): 1243–52. http://dx.doi.org/10.3397/in-2021-1787.

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Direct Acoustic Simulation (DAS) is a powerful Computational Aero Acoustics method that obtains hydrodynamic and acoustic solutions simultaneously by solving compressible Navier-Stokes equation together with state equation of ideal gas. Thus, DAS has advantages for cases with flow acoustic coupling and high Mach numbers (). With an increasing demand of massive-scale calculations, a robust numerical solver for DAS is required. ANSYS Fluent is a suitable CFD platform with proven robustness. However, there is no direct implementation of DAS in the current version of ANSYS Fluent. The present study, therefore, aims to investigate an approach for implementing DAS using ANSYS Fluent. Given the acoustic part of fluctuations is much smaller than the hydrodynamic part in amplitude, a DAS solver requires high accuracy and low dissipation. Based on these needs, proper solution methods, spatial discrete methods and boundary conditions are firstly determined through simple calculations of two dimensional propagating plane waves. Afterwards aeroacoustics of a two-dimensional cavity flow at 0.6 is calculated to verify the capability for solving separating flow with the aforementioned set-up. Finally, aeroacoustics of a cylindrical bluff body at a turbulent regime and 0.2 is calculated in three-dimensions to verify the capability for solving turbulent flow using Monotonically Integrated Large Eddy Simulation.

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11

Abdul Aziz, M. S., M. Z. Abdullah, and C. Y. Khor. "Effects of Solder Temperature on Pin Through-Hole during Wave Soldering: Thermal-Fluid Structure Interaction Analysis." Scientific World Journal 2014 (2014): 1–13. http://dx.doi.org/10.1155/2014/482363.

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An efficient simulation technique was proposed to examine the thermal-fluid structure interaction in the effects of solder temperature on pin through-hole during wave soldering. This study investigated the capillary flow behavior as well as the displacement, temperature distribution, and von Mises stress of a pin passed through a solder material. A single pin through-hole connector mounted on a printed circuit board (PCB) was simulated using a 3D model solved by FLUENT. The ABAQUS solver was employed to analyze the pin structure at solder temperatures of 456.15 K (183°C) <T< 643.15 K (370°C). Both solvers were coupled by the real time coupling software and mesh-based parallel code coupling interface during analysis. In addition, an experiment was conducted to measure the temperature difference (ΔT) between the top and the bottom of the pin. Analysis results showed that an increase in temperature increased the structural displacement and the von Mises stress. Filling time exhibited a quadratic relationship to the increment of temperature. The deformation of pin showed a linear correlation to the temperature. TheΔTobtained from the simulation and the experimental method were validated. This study elucidates and clearly illustrates wave soldering for engineers in the PCB assembly industry.

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12

Feng, Kun, Chunqing Li, Ming Zhang, and Xuting Liu. "Simulation and Computational Study of CFD on Tube MBR Membrane Assembly." Discrete Dynamics in Nature and Society 2021 (May 13, 2021): 1–8. http://dx.doi.org/10.1155/2021/5577715.

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When using tubular MBR to treat sewage, the water production is an important parameter to measure the efficiency of the tubular MBR system. The problem to be solved in this paper is to calculate the water yield of the tubular MBR system, so as to evaluate the sewage treatment efficiency of the MBR system. This research uses the CFD simulation software ANSYS 16.0 to study the water yield of the tubular MBR system. The MBR model of a single membrane filament tube was established using the ICEM CFD preprocessor in ANSYS 16.0, and the structured grid was divided to obtain a grid file. Then, the fluid solver was used to solve the mesh file and through the flow monitoring window to obtain the water output of the tubular MBR system. Finally, the CFD postprocessor in ANSYS 16.0 was used to visualize the calculation results and compare them with the waste-water treatment results of some actual MBR systems. The results show that the water yield calculated by the fluent solver is basically the same as that of the actual MBR system. This research realizes the purpose of calculating the water yield of the tubular MBR system with CFD technology, solves the problem of evaluating the working efficiency of the tubular MBR system with water consumption, and realizes the MBR before deployment The evaluation of the working efficiency of the system has certain reference value for the planning, design, and deployment of MBR.

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13

Vyroubal, Petr, and Martin Mačák. "Numerical Modeling of Cyclic Voltametry." ECS Transactions 105, no. 1 (November 30, 2021): 561–66. http://dx.doi.org/10.1149/10501.0561ecst.

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This paper deals with a new approach to numerical modeling of cyclic voltammetry using the CFD solver FLUENT. The standard use of this solver is in the field of flow and heat transfer calculations, however, it is possible to model electrochemical reactions and it also includes basic models for calculations related to batteries, such as charging and discharging processes, temperature fields, etc. Thanks to the possibility of scripting, however, it is possible to extend these tasks to a much more complex level.

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14

Abas, Aizat, N. Hafizah Mokhtar, M. H. H. Ishak, M. Z. Abdullah, and Ang Ho Tian. "Lattice Boltzmann Model of 3D Multiphase Flow in Artery Bifurcation Aneurysm Problem." Computational and Mathematical Methods in Medicine 2016 (2016): 1–17. http://dx.doi.org/10.1155/2016/6143126.

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This paper simulates and predicts the laminar flow inside the 3D aneurysm geometry, since the hemodynamic situation in the blood vessels is difficult to determine and visualize using standard imaging techniques, for example, magnetic resonance imaging (MRI). Three different types of Lattice Boltzmann (LB) models are computed, namely, single relaxation time (SRT), multiple relaxation time (MRT), and regularized BGK models. The results obtained using these different versions of the LB-based code will then be validated with ANSYS FLUENT, a commercially available finite volume- (FV-) based CFD solver. The simulated flow profiles that include velocity, pressure, and wall shear stress (WSS) are then compared between the two solvers. The predicted outcomes show that all the LB models are comparable and in good agreement with the FVM solver for complex blood flow simulation. The findings also show minor differences in their WSS profiles. The performance of the parallel implementation for each solver is also included and discussed in this paper. In terms of parallelization, it was shown that LBM-based code performed better in terms of the computation time required.

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15

Nguyen, Phu Khanh, Koichi Mori, Thi Kim Dung Hoang, Van Hoa Nguyen, and Hai Anh Nguyen. "Research on Simulation and Experiment of Dynamic Aeroelastic Analysis on Wing Structure." Applied Mechanics and Materials 798 (October 2015): 541–45. http://dx.doi.org/10.4028/www.scientific.net/amm.798.541.

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In this paper, a simulation method was realized to predict aeroelastic response and characteristic parameters of wing structure. This method was developed base on interaction between Fluent solver and Mechanical APDL solver using a coupling system in ANSYS Workbench. AGARD 445.6 wing model was chose for this developed procedure at high speed. Obtained results were compared to other numerical result and experimental results. After that, experiment was also setup in suitable conditions to study aeroelacticity characteristics and specify quantitative parameters as frequency, amplitude of oscillation, wing root forces. Final goal was comparison between numerical results and experimental results on the same wing structure at low speed.

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16

Conde, J. M. P., and M. B. S. P. Condeço. "Numerical Simulation of an Oscillating Water Column (OWC) Wave Energy Converter (WEC) on a Breakwater Using OpenFOAM^®." Defect and Diffusion Forum 396 (August 2019): 12–21. http://dx.doi.org/10.4028/www.scientific.net/ddf.396.12.

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This paper presents the application of the OpenFOAM® software package, using the IHFoam/OlaFlow solver, in the simulation of the water waves and air flow in an OWC-WEC located on a breakwater, the Mutriku power station in the north of Spain. The numerical code solves the transient Reynolds averaged Navier-Stokes (RANS) equations, using the Volume of Fluid (VoF) technique to identify the free surface. The standard k-ε turbulence model was used evaluate the Reynold stresses. Two geometries were considered: one with the pneumatic chamber completely open to the atmosphere; and other with the chamber connected to the turbine duct. The solutions obtained by OpenFOAM® are compared with those obtained by the commercial code Fluent.

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17

SEENI, Aravind, Parvathy RAJENDRAN, Mamat HUSSIN, and Farzad ISMAIL. "Errors and uncertainties in simulation of steady, viscous flow past a circular cylinder at Re = 20 using a systematic approach." INCAS BULLETIN 12, no. 3 (September 1, 2020): 203–17. http://dx.doi.org/10.13111/2066-8201.2020.12.3.17.

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The use of Computational Fluid Dynamics as a tool for design and analysis of aerospace systems is well established. Since the results generated by a CFD solver are numerical approximations, the solution is inherently produced with errors and uncertainties. In this paper, a simple fluid flow problem of laminar, incompressible flow past a circular cylinder at Reynolds number of 20 is allowed to be solved by the well-known finite-volume solver ANSYS Fluent. The effect of variations in mesh resolution, domain boundary location and residual criteria settings is investigated. For all the cases, finite, structured meshes of acceptable quality are used. The influence of variables on the cylinder’s drag results is analyzed and discussed. An interesting pattern in results has been observed. The study on the variation in mesh resolution showed no presence of mesh independent solution. The study on the variation of the domain distance showed that it is necessary to increase the diameter of the circle several thousand times to obtain a domain independent solution.

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18

Horová, Veronika, Marian Bojko, and Josef Dobeš. "Methodology of using the Adjoint solver optimization tool during flow in the intercooler filling line to minimize pressure drop." EPJ Web of Conferences 213 (2019): 02025. http://dx.doi.org/10.1051/epjconf/201921302025.

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The paper deals with numerical modelling of the flow in the intercooler filling line by Adjoint solver to minimize pressure loss. The ANSYS Fluent software was used for the calculations. The basic flow calculation was performed in the first phase. Then the mathematical model with Adjoint solver optimization tool was defined. The numerical calculation was unstable and did not lead to a convergent solution, because of creation of vortexes. The mathematical model was simplified in the second phase. To suppress instabilities and vortices a dynamic viscosity of coolant was adjusted. The pressure gradients between inlet and outlet for unmodified geometry and for modified geometry were evaluated. The final evaluations of pressure drop changes were implemented for modified geometry with original dynamic viscosity of the coolant.

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19

Peter, Ildiko, and Mario Rosso. "Simulation of Electrodeposition of Al from Ionic Liquid." Materials Science Forum 794-796 (June 2014): 229–34. http://dx.doi.org/10.4028/www.scientific.net/msf.794-796.229.

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Galvanic deposition of Aluminium on steel substrate, starting from liquid ions, is considered. How the agitation of the liquid during deposition influences the homogeneity of the developed coating layer is investigated by a commercially available FLUENT® ANSYS® solver. Comparison of data coming from numerical simulation with experimentally obtained results are presented. The reported results demonstrate that the deposition process parameter influences the quality of the deposited aluminium.

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20

Chen, Ye, Zhongxi Hou, Bingjie Zhu, Zheng Guo, and Boting Xu. "Validation for Aerodynamic Performance on Over-Expanded State of Single Expansion Ramp Nozzle Configuration." Aerospace 9, no. 11 (November 14, 2022): 715. http://dx.doi.org/10.3390/aerospace9110715.

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The performance of a single expansion ramp nozzle (SERN) drastically declines on over-expanded conditions. A numerical code can accurately predict nozzle performance in the over-expanded state, which is crucial for the SERN configuration design. A Reynolds-averaged Navier–Stokes (RANS) simulation of the SERN jet in an over-expanded state was performed to verify the numerical performance of the well-established commercial CFD solver (ANSYS FluentTM v202) and rhoCentralFoam solver in OpenFOAM. The wall pressure distributions and flow field characteristics including the shock structures and the width of the jet were studied in detail with an inlet nozzle pressure ratio (NPR) of 1.5, 3, 4, and 8. The SERN aerodynamic performance with an inlet NPR ranging from 1.5 to 9 was then calculated. The results showed that the Fluent 3D simulation could qualitatively predict the characteristics of the internal and external flow of the nozzle, because it overestimated the wall pressure and shock wave position. Two-dimensional (2D) simulations made it difficult to capture the external flow structure due to the 3D effects. The simulation results of rhoCentralFoam for over-expanded SERN flow were not ideal. The Fluent can produce physical solutions, and it achieved limited success. The existing errors were mainly caused by the inlet boundary setting.

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Czerwiński, Grzegorz, and Jerzy Wołoszyn. "Optimization of Air Cooling System Using Adjoint Solver Technique." Energies 14, no. 13 (June 23, 2021): 3753. http://dx.doi.org/10.3390/en14133753.

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Air cooling systems are currently the most popular and least expensive solutions to maintain a safe temperature in electronic devices. Heat sinks have been widely used in this area, allowing for an increase in the effective heat transfer surface area. The main objective of this study was to optimise the shape of the heat sink geometric model using the Adjoint Solver technique. The optimised shape in the context of minimal temperature value behind the heat sink is proposed. The effect of radiation and trapezoidal fin shape on the maximum temperature in the cooling system is also investigated. Simulation studies were performed in Ansys Fluent software using the Reynolds—averaged Navier–Stokes technique. As a result of the simulation, it turned out that not taking into account the radiation leads to an overestimation of temperatures in the system—even by 14 ∘C. It was found that as the angle and height of the fins increases, the temperature value behind the heat sink decreases and the heat source temperature increases. The best design in the context of minimal temperature value behind the heat sink from all analysed cases is obtained for heat sink with deformed fins according to iteration 14. The temperature reduction behind the heat sink by as much as 25 ∘C, with minor changes in heat source temperature, has been achieved.

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22

Ji, Hong, Wei Guo Zhu, Song Chen, and Jing Zhao. "Analysis of the Laminar Flow in the Hydraulic Poppet Valve Based on the Fluent 3D Solver." Applied Mechanics and Materials 385-386 (August 2013): 97–100. http://dx.doi.org/10.4028/www.scientific.net/amm.385-386.97.

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The hydraulic poppet valve is an important basic component in Fluid drive and control technology, whose characteristic of the inner flow filed influences directly the valves performance. The main work is numerical calculation and simulation of flow field inside the cone valve in the hydraulic hammer. The first step is 3d modeling of cone valve. By using fluent software the study analyses and discusses the flow field of hydraulic cone valve including flow velocity field, pressure field and flow line distribution when the valve cores cone angle is 30°, analyses the cause of the vortexes position and strength, and finds out the main reason causing energy consumption.The results of the study show that by the optimal design of the cone valve seat, the density degree of the flow and the size of the vortex is reduced, the energy loss is reduced, negative pressure zone also changes, the noise is reduced and the energy utilization is improved.

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23

Ding, F., C. B. Shen, W. Huang, and J. Liu. "Numerical validation and back-pressure effect on internal compression flows of typical supersonic inlet." Aeronautical Journal 119, no. 1215 (May 2015): 631–45. http://dx.doi.org/10.1017/s0001924000010721.

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AbstractA numerical study was conducted to analyse the performance of different turbulence models and different turbulence intensities and turbulence length scales specified for the boundary condition of the inflow to the internal compression flow field of a typical supersonic inlet. The effect of the back-pressure ratio on the properties of the flow field was also investigated. Computational results obtained by the commercial software FLUENT, which is used to solve the full two-dimensional Reynolds-averaged Navier-Stokes equations, were validated through both graphical and quantitative comparisons with previously published experimental data. The two-equation models that were considered in this study are the RNGk-ε, realisablek-ε, standardk-ε, and SSTk-ω turbulence models. The RNGk-ε model had the best performance among the four models and predicted good wall pressure distributions. The best agreement between the predicted results and experimental data was obtained when either the default values of the freestream turbulence intensity and length scale in the FLUENT solver were used, or the empirical formula was used to calculate the two parameters of the freestream turbulence properties. The shock wave pattern varied between the oblique mode and the fully developed normal mode with increasing back-pressure ratio, and the unstart phenomenon occurred when the back-pressure ratio was sufficiently high.

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24

Zuppardi, G., and D. Paterna. "Influence of rarefaction on the computation of aerodynamic parameters in hypersonic flow." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 216, no. 6 (June 1, 2002): 277–90. http://dx.doi.org/10.1243/095441002321029026.

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The results from two well-known and widely accepted codes, the Navier—Stokes solver FLUENT and the direct simulation Monte Carlo (DSMC) solver DS2G, have been analysed in order to fix the levels of the flow field rarefaction where the codes can work properly for the computation of aerodynamic forces and heat flux on a spacecraft during the re-entry. This subject has already been widely investigated; thus the purpose of the present work is to provide a further contribution. In order to make realistic computations, a probable path of a typical capsule, returning from an interplanetary mission to Earth, has been considered in the altitude range 50—120 km. Proper use of FLUENT was fixed at the free-stream Knudsen number Kn∞ < 7×10−5. Attempts have been made to increase this limit, but with no success. More specifically, a finer mesh as well as a slip velocity and temperature jump were considered. Physical conditions like the lack of isotropy of the pressure tensor and the failure of the classical phenomenological equations, both increasing with the rarefaction, are very probably the causes of the failure of FLU EN T. The basic principle of the DSMC solver is valid at each rarefaction level; a sensitivity analysis on the characteristic dimension of the cell, on the time step and on the number of simulated molecules verified that the restrictions on DS2G are imposed only by the capability of the computer. As neither experimental data nor numerical results are available at the present test conditions, the evaluation of the results relies just on qualitative considerations about the trends of experimental data, reported in the literature, of a sphere in a hypersonic transitional regime.

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25

Maram, Moloud Arian, Hamid Reza Ghafari, Hassan Ghassemi, and Mahmoud Ghiasi. "Numerical Study on the Tandem Submerged Hydrofoils Using RANS Solver." Mathematical Problems in Engineering 2021 (February 10, 2021): 1–17. http://dx.doi.org/10.1155/2021/8364980.

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This paper is presented on the tandem two-dimensional hydrofoils with profiles NACA4412 in single-phase and two-phase flow domains for different submergence depths and different distances in a various angle of attack (AoA). Also, supercavitation is studied at σ = 0.34 by the Zwart cavitation model. Reynolds-averaged Navier–Stokes (RANS) with the shear stress transport (SST) K-ω is employed as a turbulence model in transient analysis of Ansys FLUENT software. The numerical results show that, by increasing depth, the drag coefficient increases for both hydrofoils 1 and 2 as well as the lift coefficient. The drag coefficient of hydrofoil 2 is bigger than hydrofoil 1 for all depths; moreover, it was found that the flow pressure behind the hydrofoil 1 had affected the upper and the lower surface of the hydrofoil 2 at each distance or AoA. These effects are observed in the hydrofoil 2 lift coefficient as well as the flow separation. However, the maximum lift-to-drag ratio is observed at AoA = 8 ° and 3.5c distance. Also, single-phase results reveal that the value of pressure and the hydrodynamic coefficient are very different from the two-phase flow results, due to the elimination of the free surface. So, a two-phase flow domain is recommended for increasing the accuracy of results. In addition, the investigation of supercavitation shows a growth in cavity occurrence on the surface by raising AoA.

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26

Liu, Zhuoran, Caizheng Wang, Ke Zhang, Zhuo Zhao, and Zhifeng Xie. "Research on Computational Method of Supersonic Inlet/Isolator Internal Flow." Applied Sciences 11, no. 19 (October 6, 2021): 9272. http://dx.doi.org/10.3390/app11199272.

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In this research, a CFD solver is developed for solving the 2D/3D compressible flow problem: the finite volume method based on multi-block structural grids is used to solve the compressible Reynolds averaged Navier–Stokes equations (RANS). Included in the methodology are multiple high-order reconstruction schemes, such as the 3rd-order MUSCL (Monotone Upstreamcentered Schemes for Conservation Laws), 5th-order WENO (Weight Essentially Non-Oscillatory), and 5th-order MP (Monotonicity-Preserving) schemes. Of the variety of turbulence models that are embedded, this solver is mainly based on the shear stress transport model (SST), which is compatible with OpenMP/MPI parallel algorithms. This research uses the CFD solver to conduct steady-state flow simulation for a two-dimensional supersonic inlet/isolator, incorporating these high-precision reconstruction schemes to accurately capture the shock wave/expansion wave interaction and shock wave/turbulent boundary layer interaction (SWTBLI), among other effects. By comparing the 2D/3D computation results of the same inlet configuration, it is found that the 3D effects of the side wall cannot be ignored due to the existing strong lateral flow near the corner. To obtain a more refined turbulence simulation, the commercial software ANSYS Fluent 18.0 is used to carry out the detached eddy simulation (DES) and the large eddy simulation (LES) of the same supersonic inlet, so as to reveal the flow details near the separation area and boundary layers.

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27

Abdul Aziz, M. S., M. Z. Abdullah, and C. Y. Khor. "Thermal fluid-structure interaction of PCB configurations during the wave soldering process." Soldering & Surface Mount Technology 27, no. 1 (February 2, 2015): 31–44. http://dx.doi.org/10.1108/ssmt-07-2014-0013.

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Purpose – This paper aims to investigate the thermal fluid–structure interactions (FSIs) of printed circuit boards (PCBs) at different component configurations during the wave soldering process and experimental validation. Design/methodology/approach – The thermally induced displacement and stress on the PCB and its components are the foci of this study. Finite volume solver FLUENT and finite element solver ABAQUS, coupled with a mesh-based parallel code coupling interface, were utilized to perform the analysis. A sound card PCB (138 × 85 × 1.5 mm3), consisting of a transistor, diode, capacitor, connector and integrated circuit package, was built and meshed by using computational fluid dynamics pre-processing software. The volume of fluid technique with the second-order upwind scheme was applied to track the molten solder. C language was utilized to write the user-defined functions of the thermal profile. The structural solver analyzed the temperature distribution, displacement and stress of the PCB and its components. The predicted temperature was validated by the experimental results. Findings – Different PCB component configurations resulted in different temperature distributions, thermally induced stresses and displacements to the PCB and its components. Results show that PCB component configurations significantly influence the PCB and yield unfavorable deformation and stress. Practical implications – This study provides PCB designers with a profound understanding of the thermal FSI phenomenon of the process control during wave soldering in the microelectronics industry. Originality/value – This study provides useful guidelines and references by extending the understanding on the thermal FSI behavior of molten solder for PCBs. This study also explores the behaviors and influences of PCB components at different configurations during the wave soldering process.

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28

Nagy, Csaba, Arnold Rónaföldi, and András Roósz. "Comparison of Measured and Numerically Simulated Angular Velocity of Magnetically Stirred Liquid Ga-ln Alloy." Materials Science Forum 752 (March 2013): 157–66. http://dx.doi.org/10.4028/www.scientific.net/msf.752.157.

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A measurement of the angular velocity/revolution number of magnetically stirred liquid gallium-indium alloy was realized with newly developed angular velocity measuring equipment. To get additional information about the flow of the melt, a numerical simulation model was performed with ANSYS FLUENT 13.0 with a single phase 2D k-ε turbulence solver. The aim was to reproduce the flow as accurate as possible, so the measured and computed angular velocity data was compared, to see if the system can be modeled fairly well.

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29

Younoussi, Somaya, and Abdeslem Ettaouil. "Numerical Study of a Small Horizontal-Axis Wind Turbine Aerodynamics Operating at Low Wind Speed." Fluids 8, no. 7 (June 26, 2023): 192. http://dx.doi.org/10.3390/fluids8070192.

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The present work aims to study the aerodynamic characteristics of a newly designed three-bladed horizontal-axis wind turbine (HAWT) using the Computational Fluid Dynamic (CFD) method. The blade geometry is designed using an improved Blade Element Momentum (BEM) method to be similar in size to the Ampair300 wind turbine. The shear stress transport (SST) transition turbulence model closure is utilized to solve the steady state three-dimensional Reynolds Averaged Navier-Stokes (RANS) equations. The Ansys Fluent CFD solver is used to solve the problem. Then, a comparison between the two turbines’ operating conditions is conducted by monitoring the pressure coefficient, pressure contours and velocity vectors at five different radial positions. The analysis of the Tip Speed Ratio (TSR) effects on the turbine efficiency and on the flow behavior on the blade and in the near wake is carried out. For 8 m/s wind speed, the optimum pitch angle is also investigated, and the results are prepared against each TSR.

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30

Saha, Pritam, and Harshpreet Singh Kaberwal. "Numerical Analysis of Aerodynamic Performance Characteristics of NACA 2312 and NACA 2412." Volume 5 - 2020, Issue 3 - March 5, no. 3 (2020): 420–28. http://dx.doi.org/10.38124/ijisrt20mar229.

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Анотація:

Comparison of the Aerodynamic Performance characteristics of NACA 2312 and NACA 2412 aerofoils under the same flow conditions at a Reynolds number of 2.74 x 106 is presented. ANSYS is used for the creation of geometry and meshing and FLUENT is used as a solver. Coefficient of lift and coefficient of drag for both aerofoils are compared for a range of Angle of Attack while the free stream velocity of air is kept constant. This analysis can be used for the wing design and other aerodynamic modelling corresponds to these aerofoils.

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31

THIELSCHER, MICHAEL. "FLUX: A logic programming method for reasoning agents." Theory and Practice of Logic Programming 5, no. 4-5 (July 2005): 533–65. http://dx.doi.org/10.1017/s1471068405002358.

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FLUX is a programming method for the design of agents that reason logically about their actions and sensor information in the presence of incomplete knowledge. The core of FLUX is a system of Constraint Handling Rules, which enables agents to maintain an internal model of their environment by which they control their own behavior. The general action representation formalism of the fluent calculus provides the formal semantics for the constraint solver. FLUX exhibits excellent computational behavior due to both a carefully restricted expressiveness and the inference paradigm of progression.

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32

AbdelGawad, Alaa R., and Liang Guozhu. "A Numerical Simulation Study for A Dual Thrust Solid Propellant Rocket Motor Nozzle." Journal of Physics: Conference Series 2235, no. 1 (May 1, 2022): 012010. http://dx.doi.org/10.1088/1742-6596/2235/1/012010.

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Abstract CFD simulation through the rocket motor nozzle is an important issue as it gives a better understanding of the flow behavior and shows the evolution of the parameters along with the nozzle. CFD simulations using ANSYS FLUENT were conducted to model the flow through an experimental dual thrust solid rocket motor nozzle at two pressure values representing the two pressure levels. A two-dimensional axisymmetric numerical simulation was carried out using a pressure-based solver to solve the governing equation and the standard k-ε model to model the turbulence through the motor nozzle. The hot gas properties used in the simulation model were calculated using the CEA software (chemical equilibrium with applications). The parameters marched out from simulations were used to calculate the thrust values for each case. The results calculated through the numerical models compared with the experimental measurements and showed an acceptable level of accuracy.

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33

Stalewski, Wieńczysław, and Katarzyna Surmacz. "Helicopter Flight Simulation based on URANS Solver and Virtual Blade Model." Journal of KONES 26, no. 3 (September 1, 2019): 211–17. http://dx.doi.org/10.2478/kones-2019-0075.

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Abstract The methodology of simulation of a rotorcraft flight has been developed and applied to simulate several stages of flight of light helicopter. The methodology is based on coupling of several computational models of Computational Fluid Dynamics, Flight Dynamic. The essence of the methodology consists in calculation of aerodynamic forces acting on the flying rotorcraft by solving during the simulation the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. In this approach, the rotorcraft is flying inside the computational 3D mesh modelling the space filled with the air. The flight simulation procedure is completely embedded in the URANS solver ANSYS FLUENT. Flow effects caused by rotating blades of main or tail rotor are modelled by application of the developed Virtual Blade Model (VBM). In this approach, real rotors are replaced by volume discs influencing the flow field similarly as rotating blades. Time-averaged aerodynamic effects of rotating blades are modelled using momentum source terms placed inside the volume-disc zones. The momentum sources are evaluated based on the Blade Element Theory, which associates local flow parameters in the blade sections with databases of 2D-aerodynamic characteristics of these sections. Apart of the VBM module, two additional UDF modules support the simulation of helicopter flight: the module responsible for modelling of all kinematic aspects of the flight and the module gathering the momentary aerodynamic loads and solves 6 DOF-Equations describing a motion of the helicopter seen as solid body. Exemplary simulation of helicopter flight, starting from a hover, through an acceleration and fast flight until a deceleration and steep descent, has been discussed.

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34

Młynarczyk, Przemysław. "The influence of the numerical solver selection on the nozzle impulse flow simulation results." MATEC Web of Conferences 240 (2018): 03008. http://dx.doi.org/10.1051/matecconf/201824003008.

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Numerical simulations are currently used for different applications in a various fields of science. Certain solutions are not as obvious as the others while the results can give very valuable conclusions. Computational Fluid Dynamics (CFD) is one of the tools that can be used to solve different problems related with the mass and heat transfer. Nowadays it is already known that the impulse flow simulation allows to determine pressure pulsation attenuation parameters by a given geometry. However, the nozzle shape optimization method strongly depends on the numerical results obtained from the impulse flow simulation. In commercial CFD software Ansys-Fluent the obtained results depends strongly on the chosen numerical methods, especially the spatial discretization method. This is the reason to use other software as a benchmark. Alternative software FlowVision was used to perform the impulse flow simulation for the same geometries to compare the results. As there is a different problem definition in both systems the calculations, accuracy and results differ from each other. The paper describes the numerical differences between solvers. Article contains discussion about obtained results and includes hints how to avoid mistakes when user change software, especially in solving unusual CFD problems.

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35

Reshma Sett, Prathmesh Pravin Verekar, and Mohammad Zuber. "Comparative Study of Dimple Effect on Three-Dimensional Cambered Aircraft Wing." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 104, no. 2 (May 11, 2023): 115–26. http://dx.doi.org/10.37934/arfmts.104.2.115126.

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This paper focuses on aerodynamic analysis over a 3D cambered wing with dimple-like surface modification. Application of the golf ball dimples on airfoils is predicted to be a good alternative for drag reduction. A golf ball with dimples allows for smooth and controlled flight. Models of cambered wings based on NACA 2412 airfoil were created to investigate the dimple effect. A comparative study is carried out between wing models with inward and outward dimples at 50% of chord length locations. Simulations were conducted for two velocities – 30 m/s and 90 m/s and the angle of attacks varying from 0° to 20°. The study is carried out using different platforms for respective processes. Firstly, ANSYS WORKBENCH© and SOLIDWORKS© are used for the geometry creation of the wing model. Next, ANSYS FLUENT© is used for the pre-processing and solver setup stage. Then, TECPLOT©, MATLAB© and FLUENT© are used for the post-processing and analysis stage. The inward dimple showed better aerodynamics when compared with outward dimple and no dimple cases.

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36

Danaila, Sterian, Delia Teleaga, and Luiza Zavalan. "Finite Volume Particle Method for Incompressible Flows." Applied Mechanics and Materials 656 (October 2014): 72–80. http://dx.doi.org/10.4028/www.scientific.net/amm.656.72.

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This paper presents an application of the Finite Volume Particle Method to incompressible flows. The two-dimensional incompressible Navier-Stokes solver is based on Chorin’s projection method with finite volume particle discretization. The Finite Volume Particle Method is a meshless method for fluid dynamics which unifies advantages of particle methods and finite volume methods in one scheme. The method of manufactured solutions is used to examine the global discretization error and finally a comparison between finite volume particle method simulations of an incompressible flow around a fixed circular cylinder and the numerical simulations with the CFD code ANSYS FLUENT 14.0 is presented.

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37

Jia, Liyuan, Song Sang, Xiao Shi, and Fukui Shen. "Investigation on Numerical Simulation of VIV of Deep-Sea Flexible Risers." Applied Sciences 13, no. 14 (July 11, 2023): 8096. http://dx.doi.org/10.3390/app13148096.

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The vortex-induced vibration (VIV) of flexible risers is a complex fluid–structure interaction (FSI) phenomenon. In this study, we conducted a numerical simulation method based on the slicing method to study the vortex-induced vibration (VIV) of deep-sea flexible risers with different slenderness ratios and uniform flow velocities. The method combines the finite element model of the riser structure with the two-dimensional flow field slices solved by the Fluent solver. The fluid–structure interaction was realized by a self-compiled UDF program and the overset mesh technique. The numerical results were validated by comparing them with experimental data. The VIV characteristics of the riser, such as the vibration track, vibration mode, vibration frequency and wake vortex shedding mode, were analyzed. The article reveals the nonlinear dynamic features of flexible riser vibration, such as multi-frequency vibration, wide-frequency vibration and multi-modal vibration. The article also provides insights into the fluid–structure interaction mechanism of VIV of deep-sea flexible risers.

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38

Sugar, Mitchell, and Paul Slaboch. "Directivity of sound propagation from an commercial supersonic engine inlet." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 2 (August 1, 2021): 4211–18. http://dx.doi.org/10.3397/in-2021-2633.

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The effects of mean flow variations on sound propagation from an axisymmetric commercial supersonic engine inlet were studied using numerical methods. A finite element model of the inlet was constructed in Ansys Fluent and used to solve for flow fields given by different initial conditions. Results from this model were fed into the aeroacoustic solver, Actran, and used to calculate far field radiated noise as well as the directivity of that noise. The acoustic source of this noise was a plane wave of a known strength placed at the fan face. In addition to assessing the effects of mean flow on the radiated noise transfer functions, the duct modes of the model were compared across different flow regimes. Relationships between mean flow parameters and the directivity of duct modes are developed. The results of this study will be used in further studies to gain a deeper understanding of how the underlying physics which govern the system create favorable or unfavorable directivity patterns.

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39

Wang, Yun, Bing Nan Li, Zhen Ying Xu, and Yong Kang Zhang. "The Analysis of Wave Form for 3-D Wave Tank." Advanced Materials Research 463-464 (February 2012): 1392–96. http://dx.doi.org/10.4028/www.scientific.net/amr.463-464.1392.

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The 3-D numerical model of wave tank is developed considering the effects of wave generating and absorbing based on viscous fluid motion differential equations (N-S equation) and the volume of fluid (VOF) method by the use of FLUENT solver. The simulation is also made by the analysis of the existing methods of wave simulation. The wave form of the 3-D wave tank is analyzed with the result of diverse diversification at different wave location and their relationship. The flow path of each particle of the wave during the propagation is also been analyzed, which provides guidance for the wave form analysis.

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40

Karaman, Mehmet, Ibrahim Özkol, and Güven Kömürgöz. "Heat Transfer Enhancement in Turbine Blade Internal Cooling Ducts." Advanced Materials Research 1016 (August 2014): 743–47. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.743.

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Gas turbine is a type of rotary engine that consists of compressor, combustion chamber, and turbine sections. This type of engine works in the Brayton Cycle principle that is compression of atmospheric flow, combustion of air-fuel mixture and expanding high temperature combustion flow to generate power output from turbine. The aim of this study is to determine the duct geometry and flow conditions of the gas turbine blades having the internal cooling ducts that acquire highest heat transfer on turbine blades. For different design of internal duct geometries and flow conditions, Fluent solver is used and solutions are validated with Han’s experimental results.

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41

DASH, SUNIL MANOHAR, and THONG-SEE LEE. "IMPULSIVELY STARTED FLOW TOPOLOGY AROUND TANDEM ARRANGEMENT OF TWO SQUARE CYLINDER AT INCIDENCE." International Journal of Modern Physics: Conference Series 19 (January 2012): 100–108. http://dx.doi.org/10.1142/s201019451200863x.

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Numerical study of impulsively started flow over two tandem square cylinders where former cylinder is rotated at angles (0-45deg) to main stream flow direction keeping later one inline to flow stream with a separation of twice the side length of square prism between the centers of cylinders is performed using FVM code solver FLUENT 6.3.26. Temporal developments of streamlines around cylinders are studied for laminar flow regime ( Re = 100). Flow pattern formed are categories into Type-1, Type-2, Type-3 & Type-4 as per vortices growth at corresponding angle of incidence which are novel results of present study. Pressure distributions over the surface of cylinders are also monitored.

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42

Ren, Li Xia, Hong Wei Lu, and Peng Du. "Numerical Simulation Research on Coal Combustion." Advanced Materials Research 742 (August 2013): 501–5. http://dx.doi.org/10.4028/www.scientific.net/amr.742.501.

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The comparative study of numerical results on pulverized coal combustion process with CFD has become an important measure for direct engineering practice. In this paper, a combustion facility was simulated numerically with the Fluent code to investigate the process of coal combustion. Firstly, geometric models, grid and boundary type were established in the Gambit. Secondly, required models, physical properties and working conditions were chosen in the solver. Then, the important diagrams of each component displayed distinctly in the post professor. The simulation results showed that the rules of the volatile releasing and combustion processes of coke could provide important references to improve the combustion of the pulverized coal.

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43

Srivastava, Aakash, Vatsalya Tiwari, and Raj Kumar Singh. "Numerical Simulation of NACA 2415 Airfoil at Different Low Reynolds Numbers and Angles of Attack." International Journal of Advance Research and Innovation 4, no. 4 (2016): 127–33. http://dx.doi.org/10.51976/ijari.441622.

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This project simulates NACA2415 airfoil on ANSYS Workbench and ANSYS FLUENT at low Reynolds numbers at different angles of attack. This is a 2-D simulation andSpalart-Allmaras is the preferred turbulentmodel solver for this process, it yielded more results closer to experimental results when compared against K-epsilon and other turbulent models.Contours of Pressure and Velocity are presented in this paper with their inferences discussed while Plots of Coefficient of Pressure (CP) about the chord lengths along the airfoil and Coefficient of Lift (CL) are plotted to compare the CFD and the experimental results. Effect of Reynolds number and Angle of Attack is thus studied and investigated.

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44

Iaccarino, Gianluca, and Stéphane Moreau. "Natural and Forced Conjugate Heat Transfer in Complex Geometries on Cartesian Adapted Grids." Journal of Fluids Engineering 128, no. 4 (December 6, 2005): 838–46. http://dx.doi.org/10.1115/1.2201625.

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The Cartesian incompressible RANS solver with immersed boundaries, IBRANS, recently developed at Stanford, has been extended to include conjugate heat transfer modeling and used for the simulation of the electrical motor of an automotive engine cooling fan system. Such applications are particularly challenging, as they involve very complex geometries with tight tolerances and rotating parts. The new conjugate heat transfer capability of IBRANS has been verified on natural and forced convection flows. The former involves flows in enclosures around a sphere and electronic chips. The latter focuses on heated cylinders for Reynolds numbers covering flow regimes ranging for a steady laminar flow to unsteady turbulent flows. Excellent agreement is achieved with similar simulations with a conventional body-fitted solver (FLUENT 6.1) using equivalent turbulent models. First three-dimensional simulations of the flow and heat transfer within the complete electrical motor are presented. The numerical predictions of the pressure drop through the motor as a function of flow rate agree very well with the measured data over the complete operating range.

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45

Maly, Milan, Jaroslav Slama, Marcel Sapik, and Jan Jedelsky. "2D and 3D numerical modelling of internal flow of Pressure-swirl atomizer." EPJ Web of Conferences 213 (2019): 02055. http://dx.doi.org/10.1051/epjconf/201921302055.

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This paper compares 2D axisymmetric and 3D numerical models used to predict the internal flow of a pressure-swirl atomizer using a commercial software Ansys Fluent 18.1. The computed results are compared with experimental data in terms of spray cone angle (SCA), discharge coefficient (CD), internal air-core dimensions and swirl velocity profile. The swirl velocity was experimentally studied using a Laser Doppler Anemometry in a scaled transparent model of the atomizer. The internal air-core was visualized at high temporal and spatial resolution by a high-speed camera with backlit illumination. The internal flow was numerically treated as transient two-phase flow. The gas-liquid interface was captured with Volume of Fluid scheme. The numerical solver used both laminar and turbulent approach. Turbulence was modelled using k-ε, k-ω, Reynolds Stress model (RSM) and coarse Large Eddy Simulation (LES). The laminar solver was capable to predict all the parameters with an error less than 5% compared with the experimental results in both 2D and 3D simulation. However, it overpredicted the velocity of the discharged liquid sheet. The LES model performed similarly to the laminar solver, but the liquid sheet velocity was 10% lower. The two-equation models k-ε and k-ω overpredicted the turbulence viscosity and the internal air-core was not predicted.

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46

Czyż, Zbigniew, and Paweł Karpiński. "NUMERICAL ANALYSIS OF THE IMPACT OF SIDESLIP ANGLE ON LOAD OF THE GYROCOPTER STABILIZERS." Aviation 23, no. 4 (February 17, 2020): 114–22. http://dx.doi.org/10.3846/aviation.2019.11924.

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The paper presents some of the works related to the project of modern gyrocopter construction with the possibility of a short start, known as "jump-start". It also presents a methodology related to numerical calculations using Computational Fluid Dynamics based on ANSYS Fluent three-dimensional solver. The purpose of the work was to calculate the forces and aerodynamic moments acting on the gyrocopter stabilizers. The calculations were carried out for a range of angle of attack α from –20° to +25° and for a sideslip angle β from 0° to 20°. Based on the calculations carried out, analysis of the impact of the slip angle on the load on the stabilizers has been made.

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47

Kelimu, Muhetaer, Antoine Saab, Tan Tran, and Marc Thiriet. "A simple Representative Model of the Thoracic Aorta." Advanced Materials Research 33-37 (March 2008): 757–60. http://dx.doi.org/10.4028/www.scientific.net/amr.33-37.757.

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The study has been carried out in the framework of heart perfusion. The myocardium is usually irrigated by two coronary arteries, the entries of which are located in the Valsalva sinuses of the aortic root, slightly above the open leaflets of the aortic valve. The present investigation is aimed at determining a representative model of the thoracic aorta, especially of its ascending segment with the aortic valve and the coronary arteries, as well as the aortic arch, which commonly gives rise to three main branches irrigating the upper body parts, and the descending aorta. The model is developed using a CAD software and then meshed. Finally, steady flow simulations are performed using the CFD solver Fluent.

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48

Zalewski, Wiesław. "The Impact of Propeller on Aerodynamics of Aircraft / Wpływ Śmigła Na Aerodynamikę Samolotu." Journal of KONBiN 33, no. 1 (September 1, 2015): 209–22. http://dx.doi.org/10.1515/jok-2015-0018.

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Abstract The paper presents a numerical analysis of the impact of working propellers on the aerodynamics of the aircraft. Analysis was made on the example of a twin-engined, unmanned aircraft with electric drive during the low altitude flight. Three configurations were studied and compared: the plane without propellers, the plane with pusher propellers and the plane with tractor propellers. For each configuration distributions of aerodynamic coefficients along the span of the wing and their global values for the entire aircraft were estimated. Calculations were performed using the Fluent solver with implementation of a simplified model of propeller based on the Blade Element Theory. Results of the analysis indicate a slight advantage of the tractor propellers configuration.

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49

G., Prasad, Ramesh M., and Rajasekar K. "Numerical Investigation on Effect of Multiple Winglets for Wind Turbine Applications." International Journal of Engineering & Technology 7, no. 4.5 (September 22, 2018): 450. http://dx.doi.org/10.14419/ijet.v7i4.5.20204.

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The present article is an effort to examine the potential of multiple winglets to reduce the induced drag of the aerodynamic surface. The advantages of using multiple winglets include reduction of induced drag, increased L/D and improved performance of the Wind turbine. Computational Fluid Dynamics is utilized as to approach the effects of multiple winglets with NACA 24012 airfoil section for untwisted, rectangular wing. The testing of configurations is done at Reynolds number 290,000. FLUENT solver incorporated in ANSYS used for the numerical investigation of the steady flow over the wing. A substantial improvement in lift curve slope occurs with dihedral spread of the winglets. The dihedral spread also distributes the tip vortices.

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50

Abdul Aziz, M. S., M. Z. Abdullah, C. Y. Khor, M. Mazlan, A. M. Iqbal, and Z. M. Fairuz. "A computational fluid dynamics analysis of the wave soldering process." International Journal of Numerical Methods for Heat & Fluid Flow 25, no. 5 (June 1, 2015): 1231–47. http://dx.doi.org/10.1108/hff-02-2014-0053.

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Анотація:

Purpose – The purpose of this paper is to present a three-dimensional finite volume-based analysis on the effects of propeller blades on fountain flow in a wave soldering process and performs an experimental validation. Design/methodology/approach – Solder pot models with various numbers of propeller blades were developed and meshed by using hybrid elements and simulated by using the FLUENT fluid flow solver. The characteristics of the fountain, such as flow profile, velocity vector, filling time, and fountain advancement, were investigated. Molten solder (Sn63Pb37) material, a temperature of 250°C, and a propeller speed of 830 rpm were applied in the simulation. The predicted results were validated by the experimental fountain profile. Findings – The use of a six-blade propeller in a solder pot increased the fountain thickness profile and reduced the filling time. Moreover, a six-blade propeller design resulted in a stable fountain profile and was considered the best choice for current wave soldering processes. Practical implications – This study provides a better understanding of the effects of propeller blades on the fountain flow in the wave soldering process. Originality/value – The study explores the fountain flow behavior and provides a reference to the engineers and designers in order to improve the fountain flow of the wave soldering.

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