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Journal articles on the topic 'Unstructured CFD Code Optimization'

Author: Grafiati

Published: 4 June 2021

Last updated: 4 February 2022

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1

Hückelheim, Jan, Paul Hovland, Michelle Mills Strout, and Jens-Dominik Müller. "Reverse-mode algorithmic differentiation of an OpenMP-parallel compressible flow solver." International Journal of High Performance Computing Applications 33, no. 1 (2017): 140–54. http://dx.doi.org/10.1177/1094342017712060.

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Reverse-mode algorithmic differentiation (AD) is an established method for obtaining adjoint derivatives of computer simulation applications. In computational fluid dynamics (CFD), adjoint derivatives of a cost function output such as drag or lift with respect to design parameters such as surface coordinates or geometry control points are a key ingredient for shape optimization, uncertainty quantification and flow control. The computational cost of CFD applications and their derivatives makes it essential to use high-performance computing hardware efficiently, including multi- and many-core ar

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2

Amirante, Riccardo, Luciano Andrea Catalano, and Paolo Tamburrano. "The importance of a full 3D fluid dynamic analysis to evaluate the flow forces in a hydraulic directional proportional valve." Engineering Computations 31, no. 5 (2014): 898–922. http://dx.doi.org/10.1108/ec-09-2012-0221.

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Purpose – The purpose of this paper is to present a full 3D Computational Fluid Dynamics (CFD) analysis of the flow field through hydraulic directional proportional valves, in order to accurately predict the flow forces acting on the spool and to overcome the limitations of two-dimensional (2D) and simplified three-dimensional (3D) models. Design/methodology/approach – A full 3D CAD representation is proposed as a general approach to reproduce the geometry of an existing valve in full detail; then, unstructured computational grids, which identify peculiar positions of the spool travel, are gen

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KITAMURA, Keiichi, Keiichiro FUJIMOTO, Eiji SHIMA, Kazuto KUZUU, and Z. J. WANG. "Validation of Arbitrary Unstructured CFD Code for Aerodynamic Analyses." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53, no. 182 (2011): 311–19. http://dx.doi.org/10.2322/tjsass.53.311.

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Hills, N. "Achieving high parallel performance for an unstructured unsteady turbomachinery CFD code." Aeronautical Journal 111, no. 1117 (2007): 185–93. http://dx.doi.org/10.1017/s0001924000004449.

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This paper describes the work done to achieve high parallel performance for an unstructured, unsteady turbomachinery computational fluid dynamics (CFD) code. The aim of the work described here is to be able to scale problems to the thousands of processors that current and future machine architectures will provide. The CFD code is in design use in industry and is also used as a research tool at a number of universities. High parallel scalability has been achieved for a range of turbomachinery test cases, from steady-state hexahedral mesh cases to fully unsteady unstructured mesh cases. This has

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Sillén, Mattias. "Evaluation of Parallel Performance of an Unstructured CFD Code on PC-Clusters." Journal of Aerospace Computing, Information, and Communication 2, no. 1 (2005): 109–19. http://dx.doi.org/10.2514/1.13759.

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Jahangirian, A., and A. Shahrokhi. "Aerodynamic shape optimization using efficient evolutionary algorithms and unstructured CFD solver." Computers & Fluids 46, no. 1 (2011): 270–76. http://dx.doi.org/10.1016/j.compfluid.2011.02.010.

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Yamazaki, Wataru, Kisa Matsushima, and Kazuhiro Nakahashi. "Drag prediction, decomposition and visualization in unstructured mesh CFD solver of TAS-code." International Journal for Numerical Methods in Fluids 57, no. 4 (2008): 417–36. http://dx.doi.org/10.1002/fld.1643.

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8

López, D., C. Angulo, I. Fernández de Bustos, and V. García. "Framework for the Shape Optimization of Aerodynamic Profiles Using Genetic Algorithms." Mathematical Problems in Engineering 2013 (2013): 1–11. http://dx.doi.org/10.1155/2013/275091.

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This study developed a framework for the shape optimization of aerodynamics profiles using computational fluid dynamics (CFD) and genetic algorithms. A genetic algorithm code and a commercial CFD code were integrated to develop a CFD shape optimization tool. The results obtained demonstrated the effectiveness of the developed tool. The shape optimization of airfoils was studied using different strategies to demonstrate the capacity of this tool with different GA parameter combinations.

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Elham, Ali, and Michel J. L. van Tooren. "Discrete adjoint aerodynamic shape optimization using symbolic analysis with OpenFEMflow." Structural and Multidisciplinary Optimization 63, no. 5 (2021): 2531–51. http://dx.doi.org/10.1007/s00158-020-02799-7.

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AbstractThe combination of gradient-based optimization with the adjoint method for sensitivity analysis is a very powerful and popular approach for aerodynamic shape optimization. However, differentiating CFD codes is a time consuming and sometimes a challenging task. Although there are a few open-source adjoint CFD codes available, due to the complexity of the code, they might not be very suitable to be used for educational purposes. An adjoint CFD code is developed to support students for learning adjoint aerodynamic shape optimization as well as developing differentiated CFD codes. To achie

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Koten, Hasan, Mustafa Yilmaz, and M. Zafer Gul. "Compressed Biogas-Diesel Dual-Fuel Engine Optimization Study for Ultralow Emission." Advances in Mechanical Engineering 6 (January 1, 2014): 571063. http://dx.doi.org/10.1155/2014/571063.

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The aim of this study is to find out the optimum operating conditions in a diesel engine fueled with compressed biogas (CBG) and pilot diesel dual-fuel. One-dimensional (1D) and three-dimensional (3D) computational fluid dynamics (CFD) code and multiobjective optimization code were employed to investigate the influence of CBG-diesel dual-fuel combustion performance and exhaust emissions on a diesel engine. In this paper, 1D engine code and multiobjective optimization code were coupled and evaluated about 15000 cases to define the proper boundary conditions. In addition, selected single diesel

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Thum, Susanne, and Rudolf Schilling. "Optimization of Hydraulic Machinery Bladings by Multilevel CFD Techniques." International Journal of Rotating Machinery 2005, no. 2 (2005): 161–67. http://dx.doi.org/10.1155/ijrm.2005.161.

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The numerical design optimization for complex hydraulic machinery bladings requires a high number of design parameters and the use of a precise CFD solver yielding high computational costs. To reduce the CPU time needed, a multilevel CFD method has been developed. First of all, the 3D blade geometry is parametrized by means of a geometric design tool to reduce the number of design parameters. To keep geometric accuracy, a special B-spline modification technique has been developed. On the first optimization level, a quasi-3D Euler code (EQ3D) is applied. To guarantee a sufficiently accurate res

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Woodgate, M. A., and G. N. Barakos. "An implicit hybrid method for the computation of rotorcraft flows." Aeronautical Journal 122, no. 1256 (2018): 1522–56. http://dx.doi.org/10.1017/aer.2018.108.

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ABSTRACTThere is a wide variety of CFD grid types including Cartesian, structured, unstructured and hybrids, as well as, numerous methodologies of combining these to reduce the time required to generate high-quality grids around complex configurations. If the grid methodologies were implemented in different codes, they should be written in such a way as to obtain the maximum performance from the available computer resources. A common interface should also be required to allow for ease of use. However, it is very time consuming to develop, maintain and add extra functionally to different codes.

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Shepel, Sergey V., Brian L. Smith, and Samuel Paolucci. "Implementation of a Level Set Interface Tracking Method in the FIDAP and CFX-4 Codes." Journal of Fluids Engineering 127, no. 4 (2005): 674–86. http://dx.doi.org/10.1115/1.1949636.

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We present a streamline-upwind–Petrov-Galerkin (SUPG) finite element level set method that may be implemented into commercial computational fluid dynamics (CFD) software, both finite element (FE) and finite volume (FV) based, to solve problems involving incompressible, two-phase flows with moving interfaces. The method can be used on both structured and unstructured grids. Two formulations are given. The first considers the coupled motion of the two phases and is implemented within the framework of the commercial CFD code CFX-4. The second can be applied for those gas-liquid flows for which ef

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Siow, C. L., Jaswar, and Efi Afrizal. "Computational Fluid Dynamic Using Parallel Loop of Multi-Cores Processor." Applied Mechanics and Materials 493 (January 2014): 80–85. http://dx.doi.org/10.4028/www.scientific.net/amm.493.80.

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Computational Fluid Dynamics (CFD) software is often used to study fluid flow and structures motion in fluids. The CFD normally requires large size of arrays and computer memory and then caused long execution time. However, Innovation of computer hardware such as multi-cores processor provides an alternative solution to improve this programming performance. This paper discussed loop parallelize multi-cores processor for optimization of sequential looping CFD code. This loop parallelize CFD was achieved by applying multi-tasking or multi-threading code into the original CFD code which was devel

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Nakisa, Mehdi, Adi Maimun Abdul Malik, Yasser M. Ahmed, et al. "Propeller Effect on 3D Flow at the Stern Hull of a LNG Carrier Using Finite Volume Method." Applied Mechanics and Materials 554 (June 2014): 566–70. http://dx.doi.org/10.4028/www.scientific.net/amm.554.566.

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Numerical study and RANS simulations have been applied to investigate the incompressible free surface flow around the stern hull of Liquefied Natural Gas (LNG) ship affected by working propeller behind of her. Experimental works are carried out using LNG ship model in Marine Teknologi Center (MTC) of Univrsiti Teknologi Malaysia (UTM) to verify the computational fluid dynamic (CFD) results. Ansys-CFX 14.0 based on viscous flow finite volume code using the two-phase Eulerian–Eulerian fluid approach and shear stress transport (SST) turbulence model have been used in this study. A tetrahedral uns

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16

Adami, P., and 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, no. 2 (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

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17

Cen, Zhuo Lun, Ji Gang Zhao, and Ben Xian Shen. "Study on Inner Vortex in a Hydrocyclone through Numerical Simulation." Advanced Materials Research 788 (September 2013): 228–32. http://dx.doi.org/10.4028/www.scientific.net/amr.788.228.

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Hydrocyclones provide an economic and efficient process of separation in many industries, but there has been little detailed understanding of the strong swirling flow prevailing inside the device, especially the complex inner vortex. This work presented a computational fluid dynamics (CFD) simulation to predict and to evaluate the effects of inlet velocity and the diameter of overflow tube on the inner vortex. The calculation was carried out using commercial CFD code Ansys Fluent 14.0. The results obtained demonstrates both an overlarge inlet velocity and a too small diameter of overflow tube

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18

CHEN, LONG, YIZHAO WU, and JIAN XIA. "AEROELASTIC ANALYSIS OF ROTOR BLADES USING CFD/CSD COUPLING IN HOVER MODE." Modern Physics Letters B 24, no. 13 (2010): 1307–10. http://dx.doi.org/10.1142/s0217984910023499.

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A computational fluid dynamics (CFD) is coupled with a computational structural dynamics (CSD) to simulate the unsteady rotor flow with aeroelasticity effects. An unstructured upwind Navier-Stokes solver was developed for this simulation, with 2nd order time-accurate dual-time stepping method for temporal discretization and low Mach number preconditioning method. For turbulent flows, both the Spalart-Allmaras and Menter's SST model are available. Mesh deformation is achieved through a fast dynamic grid method called Delaunay graph map method for unsteady flow simulation. The rotor blades are m

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Tannous, A. "Optimization of a Minienvironment Design Using Computational Fluid Dynamics." Journal of the IEST 40, no. 1 (1997): 29–34. http://dx.doi.org/10.17764/jiet.2.40.1.b1762603371140r7.

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This paper discusses the use of a CFD (computational fluid dynamics) code for the design and optimization processes of a minienvironment mounted on a wafer process tool. The three-dimensional code was used to predict the air velocity flied and pressure distribution in the minienvironment based on a finite volume approach. The geometric model consists of the minienvironment, the tool surface, and the integrated I/O Indexer interfaces. The airflow in the minienvironment (with a conceptual design configuration) was simulated. The results prompted a design change. The new design has a desirable ai

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Selma, Brahim, Martin Désilets, and Pierre Proulx. "Optimization of an industrial heat exchanger using an open-source CFD code." Applied Thermal Engineering 69, no. 1-2 (2014): 241–50. http://dx.doi.org/10.1016/j.applthermaleng.2013.11.054.

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Oh, H. W., and E. S. Yoon. "Hydrodynamically detailed performance analysis of a mixed-flow waterjet pump using computational fluid dynamics." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 222, no. 9 (2008): 1861–67. http://dx.doi.org/10.1243/09544062jmes1107.

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The hydrodynamic design optimization and performance analysis of a mixed-flow waterjet pump have been achieved using the validated commercial computational fluid dynamics (CFD) code. The detailed flow field in the waterjet pump is investigated by the CFD code adopted in the present study. Predicted characteristic curves, including the cavitation performance, agree very well with the test data for a designed mixed-flow waterjet pump over the entire operating conditions. A hydraulically detailed performance analysis with a net positive suction head can be used efficiently as a tool for the pract

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Сентябов, А. В., А. А. Гаврилов, М. А. Кривов, А. А. Дектерев, and М. Н. Притула. "Efficiency analysis of hydrodynamic calculations on GPU and CPU clusters." Numerical Methods and Programming (Vychislitel'nye Metody i Programmirovanie), no. 3 (September 20, 2016): 329–38. http://dx.doi.org/10.26089/nummet.v17r331.

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Рассматривается ускорение параллельных гидродинамических расчетов на кластерах с CPU- и GPU-узлами. Для тестирования используется собственный CFD-код SigmaFlow, портированный для расчетов на графических ускорителях с помощью технологии CUDA. Алгоритм моделирования течения несжимаемой жидкости основан на SIMPLE-подобной процедуре и дискретизации с помощью метода контрольного объема на неструктурированных сетках из тексаэдральных ячеек. Сравнение скорости расчета показывает высокую производительность графических ускорителей нового поколения в GPGPU-расчетах. Speedup of parallel hydrodynamic calc

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23

Mani, M., A. Naghib-Lahouti, and M. Nazarinia. "Experimental and numerical aerodynamic analysis of a satellite launch vehicle with strap-on boosters." Aeronautical Journal 108, no. 1085 (2004): 379–87. http://dx.doi.org/10.1017/s0001924000005194.

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Abstract Results of numerical simulation of inviscid compressible flow around a generic satellite launch vehicle (SLV) with strap-on boosters using a commercial computational fluid dynamics (CFD) code named Star-CD are experimentally evaluated. Governing equations of flow around the SLV with two and two strap-on boosters were solved in three dimensions using the SIMPLE algorithm in an unstructured tetrahedral mesh, to determine longitudinal aerodynamic coefficients and surface pressure distribution at Mach numbers from 0·6 to 2·0, and angles-of-attack from 0° to 16°. To evaluate the numerical

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Riesmeier, E., S. Honnet, and N. Peters. "Flamelet Modeling of Pollutant Formation in a Gas Turbine Combustion Chamber Using Detailed Chemistry for a Kerosene Model Fuel." Journal of Engineering for Gas Turbines and Power 126, no. 4 (2004): 899–905. http://dx.doi.org/10.1115/1.1787507.

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Combustion and pollutant formation in a gas turbine combustion chamber is investigated numerically using the Eulerian particle flamelet model. The code solving the unsteady flamelet equations is coupled to an unstructured computational fluid dynamics (CFD) code providing solutions for the flow and mixture field from which the flamelet parameters can be extracted. Flamelets are initialized in the fuel-rich region close to the fuel injectors of the combustor. They are represented by marker particles that are convected through the flow field. Each flamelet takes a different pathway through the co

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Zhang, Hong Ming, and Li Xiang Zhang. "Numerical Prediction of Sediment Erosion on Francis Turbine Blades." Advanced Materials Research 662 (February 2013): 643–47. http://dx.doi.org/10.4028/www.scientific.net/amr.662.643.

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The paper presents the numerical prediction of sediment erosion on Francis turbine blades using CFD code. The 3-D turbulent particulate-liquid two-phase flow equations are employed in this study. The computing domain is discretized with a full three-dimensional mesh system of unstructured tetrahedral shapes. The finite volume method is used to solve the governing equations and the pressure-velocity coupling is handled via a Pressure Implicit with Splitting of Operators (PISO) procedure. Simulation results have shown that the sand erosion rate on pressure side is more than on the suction side o

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Karpuk, Stanislav, Yaolong Liu, and Ali Elham. "Multi-Fidelity Design Optimization of a Long-Range Blended Wing Body Aircraft with New Airframe Technologies." Aerospace 7, no. 7 (2020): 87. http://dx.doi.org/10.3390/aerospace7070087.

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The German Cluster of Excellence SE²A (Sustainable and Energy Efficient Aviation) is established in order to investigate the influence of game-changing technologies on the energy efficiency of future transport aircraft. In this paper, the preliminary investigation of the four game-changing technologies active flow control, active load alleviation, boundary layer ingestion, and novel materials and structure concepts on the performance of a long-range Blended Wing Body (BWB) aircraft is presented. The BWB that was equipped with the mentioned technologies was designed and optimized using the mult

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Alawadhi, Khaled, Yousef Alhouli, Ali Ashour, and Abdullah Alfalah. "Design and Optimization of a Radial Turbine to Be Used in a Rankine Cycle Operating with an OTEC System." Journal of Marine Science and Engineering 8, no. 11 (2020): 855. http://dx.doi.org/10.3390/jmse8110855.

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Design and optimization of a radial turbine for a Rankine cycle were accomplished ensuring higher thermal efficiency of the system despite the low turbine inlet temperature. A turbine design code (TDC) based on the meanline design methodology was developed to construct the base design of the turbine rotor. Best design practices for the base design were discussed and adopted to initiate a robust optimization procedure. The baseline design was optimized using the response surface methodology and by coupling it with the genetic algorithm. The design variables considered for the study are rotation

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Rulik, Sebastian, Włodzimierz Wróblewski, and Daniel Frączek. "Metamodel-Based Optimization of the Labyrinth Seal." Archive of Mechanical Engineering 64, no. 1 (2017): 75–91. http://dx.doi.org/10.1515/meceng-2017-0005.

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Abstract The presented paper concerns CFD optimization of the straight-through labyrinth seal with a smooth land. The aim of the process was to reduce the leakage flow through a labyrinth seal with two fins. Due to the complexity of the problem and for the sake of the computation time, a decision was made to modify the standard evolutionary optimization algorithm by adding an approach based on a metamodel. Five basic geometrical parameters of the labyrinth seal were taken into account: the angles of the seal’s two fins, and the fin width, height and pitch. Other parameters were constrained, in

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Craig, K. J., D. J. de Kock, and P. Gauche´. "Minimization of Heat Sink Mass Using CFD and Mathematical Optimization." Journal of Electronic Packaging 121, no. 3 (1999): 143–47. http://dx.doi.org/10.1115/1.2792676.

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This paper describes the use of CFD and mathematical optimization to minimise heat sink mass given a maximum allowable heat sink temperature, a constant cooling fan power and heat source. Heat sink designers have to consider a number of conflicting parameters. Heat transfer is influenced by, amongst others, heat sink properties (such as surface area), airflow bypass and the location of heat sources, whilst size and/or mass of the heat sink needs to be minimized. This multiparameter problem lends itself naturally to optimization techniques. In this study a commercial CFD code, STAR-CD, is linke

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Tsoutsanis, Panagiotis, Antonis F. Antoniadis, and Karl W. Jenkins. "Improvement of the computational performance of a parallel unstructured WENO finite volume CFD code for Implicit Large Eddy Simulation." Computers & Fluids 173 (September 2018): 157–70. http://dx.doi.org/10.1016/j.compfluid.2018.03.012.

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Wang, Bao Qing, Yang Yang Li, Rong Hui Chen, Ze Bei Wang, and Shu Yao. "CFD Analysis of Shrouded Diameter in Aerosol Sampling Inlet." Applied Mechanics and Materials 482 (December 2013): 359–62. http://dx.doi.org/10.4028/www.scientific.net/amm.482.359.

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This paper presents CFD analysis of shrouded diameter in aerosol sampling inlet. Different shrouded diameter for the sampling inlet will be simulated and discussed in detail. The objective of the design is to optimizing the sampling inlet flow necessary for achieving high efficiency of aerosol sampling, while minimizing disturbance to the aircraft which carries aerosol sampling inlet. The design optimization was performed with the computational fluid dynamics (CFD) code FLUENT. The shrouded diameter to minimizing flow disturbance is 150mm. A shrouded diameter understanding derived from the CFD

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Doupník, Petr, and Tomáš Koutník. "Validation Task for Solution of Optimal Slotted Flap Position Using Fluent Software." Applied Mechanics and Materials 821 (January 2016): 10–15. http://dx.doi.org/10.4028/www.scientific.net/amm.821.10.

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CFD solvers are commonly used in optimization problems in aerodynamics. Typical task is the search for optimal position of slotted flap. On the example is shown that the optimum predicted by CFD software can differ significantly from that found in the wind tunnel. Then the focus is on the optimal position of slotted flaps. It was examined with ANSYS Fluent CFD code with both 2D and 3D structured meshes and three different models of turbulence. Results from CFD and those of wind tunnel were compared with relevant disagreement found. Possible sources of the error are discussed and topics for fur

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Gordon, R., and Y. Levy. "Optimization of Wall Cooling in Gas Turbine Combustor Through Three-Dimensional Numerical Simulation." Journal of Engineering for Gas Turbines and Power 127, no. 4 (2005): 704–23. http://dx.doi.org/10.1115/1.1808432.

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This paper is concerned with improving the prediction reliability of CFD modeling of gas turbine combustors. CFD modeling of gas turbine combustors has recently become an important tool in the combustor design process, which till now routinely used the old “cut and try” design practice. Improving the prediction capabilities and reliability of CFD methods will reduce the cycle time between idea and a working product. The paper presents a 3D numerical simulation of the BSE Ltd. YT-175 engine combustor, a small, annular, reversal flow type combustor. The entire flow field is modeled, from the com

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Putko, Michele M., Arthur C. Taylor ,, Perry A. Newman, and Lawrence L. Green. "Approach for Input Uncertainty Propagation and Robust Design in CFD Using Sensitivity Derivatives1." Journal of Fluids Engineering 124, no. 1 (2001): 60–69. http://dx.doi.org/10.1115/1.1446068.

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An implementation of the approximate statistical moment method for uncertainty propagation and robust optimization for quasi 1-D Euler CFD code is presented. Given uncertainties in statistically independent, random, normally distributed input variables, first-and second-order statistical moment procedures are performed to approximate the uncertainty in the CFD output. Efficient calculation of both first- and second-order sensitivity derivatives is required. In order to assess the validity of the approximations, these moments are compared with statistical moments generated through Monte Carlo s

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Zhang, Hong Ming, and Li Xiang Zhang. "Numerical Prediction of Cavitation Erosion on a Francis Turbine Runner." Advanced Materials Research 655-657 (January 2013): 449–56. http://dx.doi.org/10.4028/www.scientific.net/amr.655-657.449.

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The paper presents numerical prediction of cavitation erosion on a Francis turbine runner using CFD code. The SST turbulence model is employed in the Reynolds averaged Navier–Stokes equations in this study. A mixture assumption and a finite rate mass transfer model were introduced. The computing domain is discretized with a full three-dimensional mesh system of unstructured tetrahedral shapes. The finite volume method is used to solve the governing equations of the mixture model and the pressure-velocity coupling is handled via a Pressure Implicit with Splitting of Operators(PISO) procedure. C

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Bogdanov, P. B., A. V. Gorobets, and S. A. Sukov. "Adaptation and optimization of basic operations for an unstructured mesh CFD algorithm for computation on massively parallel accelerators." Computational Mathematics and Mathematical Physics 53, no. 8 (2013): 1183–94. http://dx.doi.org/10.1134/s0965542513080046.

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Shang, Zhi. "Large-Scale CFD Parallel Computing Dealing with Massive Mesh." Journal of Engineering 2013 (2013): 1–6. http://dx.doi.org/10.1155/2013/850148.

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In order to run CFD codes more efficiently on large scales, the parallel computing has to be employed. For example, in industrial scales, it usually uses tens of thousands of mesh cells to capture the details of complex geometries. How to distribute these mesh cells among the multiprocessors for obtaining a good parallel computing performance (HPC) is really a challenge. Due to dealing with the massive mesh cells, it is difficult for the CFD codes without parallel optimizations to handle this kind of large-scale computing. Some of the open source mesh partitioning software packages, such as Me

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Huque, Ziaul, Ghizlane Zemmouri, Donald Harby, and Raghava Kommalapati. "Optimization of Wind Turbine Airfoil Using Nondominated Sorting Genetic Algorithm and Pareto Optimal Front." International Journal of Chemical Engineering 2012 (2012): 1–9. http://dx.doi.org/10.1155/2012/193021.

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A Computational Fluid Dynamics (CFD) and response surface-based multiobjective design optimization were performed for six different 2D airfoil profiles, and the Pareto optimal front of each airfoil is presented. FLUENT, which is a commercial CFD simulation code, was used to determine the relevant aerodynamic loads. The Lift Coefficient (CL) and Drag Coefficient (CD) data at a range of 0°to 12°angles of attack (α) and at three different Reynolds numbers (Re=68,459, 479, 210, and 958, 422) for all the six airfoils were obtained. Realizablek-εturbulence model with a second-order upwind solution m

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Oh, H. W., E. S. Yoon, M. R. Park, K. Sun, and C. M. Hwang. "Hydrodynamic design and performance analysis of a centrifugal blood pump for cardiopulmonary circulation." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 7 (2005): 525–32. http://dx.doi.org/10.1243/095765005x31108.

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This paper presents the hydrodynamic design and performance analysis method for a miniaturized centrifugal blood pump using three-dimensional computational fluid dynamics (CFD) code. In order to obtain the hydraulically high efficient configuration of a miniaturized centrifugal blood pump for cardiopulmonary circulation, well-established commercial CFD codes were incorporated considering detailed flow dynamic phenomena in the blood pump system. A prototype of centrifugal blood pump developed by the present design and analysis method has been tested in the mock circulatory system. Predicted res

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Zhang, Hong Ming, and Li Xiang Zhang. "Numerical Analysis of Erosive Wear on the Guide Vanes of a Francis Turbine." Applied Mechanics and Materials 741 (March 2015): 531–35. http://dx.doi.org/10.4028/www.scientific.net/amm.741.531.

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The paper presents the numerical analysis of erosive wear on the guide vanes of a Francis turbine using CFD code. The 3-D turbulent particulate-liquid two-phase flow equations are employed in this study. The computing domain is discretized with a full three-dimensional mesh system of unstructured tetrahedral shapes. The finite volume method is used to solve the governing equations and the pressure-velocity coupling is handled via a Pressure Implicit with Splitting of Operators (PISO) procedure. Simulation results have shown that the volume fraction of sand at the top of the guide vanes is high

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Gel, Aytekin, Jonathan Hu, ElMoustapha Ould-Ahmed-Vall, and Alexander A. Kalinkin. "Modernization and optimization of a legacy open-source CFD code for high-performance computing architectures." International Journal of Computational Fluid Dynamics 31, no. 2 (2017): 122–33. http://dx.doi.org/10.1080/10618562.2017.1285398.

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Yan, Chen, Ying Li, Bei Yue Ma, and Ying Ying Zhai. "Optimization Design for Structure of a Shroud Base on Fluent." Advanced Materials Research 753-755 (August 2013): 1184–87. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1184.

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This paper reports a CFD modeling study on the optimization design for the shroud structure of a three-phase electroslag furnace using double electrode series technique by a commercial code FLUENT. The Realizablekεturbulence model, Do radiation model and Mixture model are amply used to compute the flow of gases in the furnace under different entrance layouts of the shroud, and the influence of entrance layout on the air volume fraction in the furnace is obtained. Finally, a suited suggestion on the entrance layout of shroud is presented that ring topologies should be adopted.

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Park, Donghun, Yunggyo Lee, Taehwan Cho, and Cheolwan Kim. "Design and Performance Evaluation of Propeller for Solar-Powered High-Altitude Long-Endurance Unmanned Aerial Vehicle." International Journal of Aerospace Engineering 2018 (August 1, 2018): 1–23. http://dx.doi.org/10.1155/2018/5782017.

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Design, wind tunnel test, computational fluid dynamics (CFD) analysis, and flight test data analysis are conducted for the propeller of EAV-3, which is a solar-powered high-altitude long-endurance unmanned aerial vehicle developed by Korea Aerospace Research Institute. The blade element momentum theory, in conjunction with minimum induced loss, is used as a basic design method. Airfoil data are obtained from CFD analysis, which takes into account the low Reynolds number effect. The response surface is evaluated for design variables by using design of experiment and kriging metamodel. The optim

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Xing-Kaeding, Yan, and Apostolos Papanikolaou. "Optimization of the Propulsive Efficiency of a Fast Catamaran." Journal of Marine Science and Engineering 9, no. 5 (2021): 492. http://dx.doi.org/10.3390/jmse9050492.

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The present study deals with the local optimization of the stern area and of the propulsive efficiency of a battery-driven, fast catamaran vessel. The adopted approach considers a parametric model for the catamaran’s innovative transom stern and a QCM (Quasi-Continuous Method) body-force model for the effect of the fitted propellers. Hydrodynamic calculations were performed by the CFD code FreSCO+, which also enabled a deep analysis of the incurring unique propulsive phenomena. Numerical results of achieved high propulsive efficiency were verified by model experiments at the Hamburgische Schif

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Lisý, Martin, Jiří Pospíšil, Otakar Štelcl, and Michal Špilaček. "Optimization of Secondary Air Distribution in Biomass Boiler by CFD Analysis." Applied Mechanics and Materials 832 (April 2016): 231–37. http://dx.doi.org/10.4028/www.scientific.net/amm.832.231.

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This paper deals with a use of CFD modelling for optimization of supply of secondary combustion air in the two-chamber biomass boiler combusting very wet biomass (capacity ca. 200 kW). Objective of the analyse is to observe the impact of diameter of a secondary air supply pipe and air flow velocity on mixing of the secondary air with flue gas in the combustion chamber. The numerical model of the experimental boiler was build up for subsequent utilizing of CFD computation based on finite element method. The commercial code STAR-CD was used for carried out parametrical studies. Series of calcula

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Schnoes, Markus, Christian Voß, and Eberhard Nicke. "Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils." Journal of the Global Power and Propulsion Society 2 (October 18, 2018): W5N91I. http://dx.doi.org/10.22261/jgpps.w5n91i.

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The basic tool set to design multi-stage axial compressors consists of fast codes for throughflow and blade-to-blade analysis. Detailed blade row design is conducted with 3D CFD, mainly to control the end wall flow. This work focuses on the interaction between throughflow and blade-to-blade design and the transition to 3D CFD. A design strategy is presented that is based on a versatile airfoil family. The new class of airfoils is generated by optimizing a large number of airfoil shapes for varying design requirements. Each airfoil geometry satisfies the need for a wide working range as well as

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Tong, Bao Hong, Jun Yin, and Yin Liu. "CFD and Neural Network-Based Predicting for Oil Delivery Performance of Oil Pump in Engines." Advanced Materials Research 230-232 (May 2011): 784–88. http://dx.doi.org/10.4028/www.scientific.net/amr.230-232.784.

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Oil delivery pefromance of oil pump in engines are investigated by a new prediction method based on computational fluid dynamic (CFD) and artificial neural network (ANN). CFD analysis was done by using Fluent commercial code and distribution of velocity of pump’s internal flow field was achieved by the solving of pump’s CFD model. Infromation data about oil pump’s rotate speed, supplying pressure, oil temperature and oil flow rate were obtained by CFD simulation analyzing. ANN model that used to describe the delivery performance of oil pump was employed, and the model was trained by learning s

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Gao, Song, Jory Seguin, Wagdi G. Habashi, Dario Isola, and Guido Baruzzi. "A finite element solver for hypersonic flows in thermo-chemical non-equilibrium, Part II." International Journal of Numerical Methods for Heat & Fluid Flow 30, no. 2 (2019): 575–606. http://dx.doi.org/10.1108/hff-12-2018-0725.

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Purpose This work aims to describe the physical and numerical modeling of a CFD solver for hypersonic flows in thermo-chemical non-equilibrium. This paper is the second of a two-part series that concerns the application of the solver introduced in Part I to adaptive unstructured meshes. Design/methodology/approach The governing equations are discretized with an edge-based stabilized finite element method (FEM). Chemical non-equilibrium is simulated using a laminar finite-rate kinetics, while a two-temperature model is used to account for thermodynamic non-equilibrium. The equations for total q

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Akram, Md Tausif, and Man-Hoe Kim. "CFD Analysis and Shape Optimization of Airfoils Using Class Shape Transformation and Genetic Algorithm—Part I." Applied Sciences 11, no. 9 (2021): 3791. http://dx.doi.org/10.3390/app11093791.

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This paper presents the parameterization and optimization of two well-known airfoils. The aerodynamic shape optimization investigation includes the subsonic (NREL S-821) and transonic airfoils (RAE-2822). The class shape transformation is employed for parametrization while the genetic algorithm is used for optimization purposes. The absolute scheme of the optimization process is carried out for the minimization of the drag coefficient and maximization of lift to drag ratio. In-house MATLAB code is incorporated with a genetic algorithm to calculate the drag coefficient and lift to drag ratio of

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Keane, A. J., and J. P. Scanlan. "Design search and optimization in aerospace engineering." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 365, no. 1859 (2007): 2501–29. http://dx.doi.org/10.1098/rsta.2007.2019.

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In this paper, we take a design-led perspective on the use of computational tools in the aerospace sector. We briefly review the current state-of-the-art in design search and optimization (DSO) as applied to problems from aerospace engineering, focusing on those problems that make heavy use of computational fluid dynamics (CFD). This ranges over issues of representation, optimization problem formulation and computational modelling. We then follow this with a multi-objective, multi-disciplinary example of DSO applied to civil aircraft wing design, an area where this kind of approach is becoming

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