Relevant bibliographies by topics / Computational fluid dynamics analysis of a sweeper

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Computational fluid dynamics analysis of a sweeper'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Computational fluid dynamics analysis of a sweeper"

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Xin, Yu Hua, Hao Li, and Jun Jie Wu. "Applications of CFD Technique in the Flow Field Analysis of Road Sweeper." Applied Mechanics and Materials 733 (February 2015): 583–86. http://dx.doi.org/10.4028/www.scientific.net/amm.733.583.

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Application of computational fluid dynamics (CFD) in the design of the road sweeper is a new and effective method for the feasibility analysis. By using CFD technology to analyze the flow field of the road sweeper airstream system, we can obtain the characteristic parameters before it is manufactured, so that the analysis and design of the airstream system can be carried out simultaneously. Studies have shown that combining with the specific engineering practice, the application of CFD on the flow field simulation has a certain reference value for the design and optimization of the sweeper airstream system.
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Drofelnik, Jernej, Andrea Da Ronch, Matteo Franciolini, and Andrea Crivellini. "Fast identification of transonic buffet envelope using computational fluid dynamics." Aircraft Engineering and Aerospace Technology 91, no. 2 (2019): 309–16. http://dx.doi.org/10.1108/aeat-01-2018-0057.

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Purpose This paper aims to present a numerical method based on computational fluid dynamics that allows investigating the buffet envelope of reference equivalent wings at the equivalent cost of several two-dimensional, unsteady, turbulent flow analyses. The method bridges the gap between semi-empirical relations, generally dominant in the early phases of aircraft design, and three-dimensional turbulent flow analyses, characterised by high costs in analysis setups and prohibitive computing times. Design/methodology/approach Accuracy in the predictions and efficiency in the solution are two key aspects. Accuracy is maintained by solving a specialised form of the Reynolds-averaged Navier–Stokes equations valid for infinite-swept wing flows. Efficiency of the solution is reached by a novel implementation of the flow solver, as well as by combining solutions of different fidelity spatially. Findings Discovering the buffet envelope of a set of reference equivalent wings is accompanied with an estimate of the uncertainties in the numerical predictions. Just over 2,000 processor hours are needed if it is admissible to deal with an uncertainty of ±1.0° in the angle of attack at which buffet onset/offset occurs. Halving the uncertainty requires significantly more computing resources, close to a factor 200 compared with the larger uncertainty case. Practical implications To permit the use of the proposed method as a practical design tool in the conceptual/preliminary aircraft design phases, the method offers the designer with the ability to gauge the sensitivity of buffet on primary design variables, such as wing sweep angle and chord to thickness ratio. Originality/value The infinite-swept wing, unsteady Reynolds-averaged Navier–Stokes equations have been successfully applied, for the first time, to identify buffeting conditions. This demonstrates the adequateness of the proposed method in the conceptual/preliminary aircraft design phases.
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Xi, Yuan, Yan Dai, Xi–long Zhang, and Xing Zhang. "Prediction of Particle-Collection Efficiency for Vacuum-Blowing Cleaning System Based on Operational Conditions." Processes 8, no. 7 (2020): 809. http://dx.doi.org/10.3390/pr8070809.

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The dust-collection system, as the core of a sweeper vehicle, directly inhales dust particles on the pavement. The influence of variable operational conditions on particle-separation performance was investigated using computational fluid dynamics (CFD) Euler–Lagrange multiphase model. The particle-separation performance efficiency and retention time were used to evaluate the dust-collection efficiency. The uniform design (UD) and multiple regression analysis (MRA) methods were employed to predict and optimize the effects of reverse-blowing flow rate, pressure drop, and traveling speed on separation efficiency. The results indicated that the dust-collection performance initially increased and then decreased with increasing reverse-blowing flow rate. As the pressure drop increased, there was an increase in total dust-collection efficiency. However, the efficiency decreased with increasing traveling speed. The regression model showed that the proposed approach was able to predict the particle collection efficiency accurately. In addition, the optimum operational conditions were obtained, namely a reverse-blowing flow rate of 2100 m3/h, a traveling speed of 5 km/h, and a pressure drop of 2400 Pa. The maximum particle-separation efficiency was 99.10%, which showed good agreement with the experimental results.
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Xi, Yuan, Yong-liang Zhang, Xi-long Zhang, and Yan Dai. "Enhancement of particle collection efficiency considering the structural interplay: particle motion characteristics analysis." Mechanics & Industry 21, no. 6 (2020): 618. http://dx.doi.org/10.1051/meca/2020093.

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The vacuum-blowing cleaning system, utilizing positive and negative pressure mixed-delivery theory, has been adopted for the road sweeper vehicle. To enhance the solid particle separation performance and to evaluate the motion characteristics of inhaled particles under different structural parameters, the gas-solid flow in the vacuum-blowing cleaning system was investigated by using computational fluid dynamics (CFD) technology. The influence of the main structural parameters on the grade dust collection efficiency and average detention time of the inhaled particles was determined, such as suction-inlet diameter, suction-inlet inclination angle, and front baffle inclination angle. And the interplay between them was also investigated. In addition, a dust collection efficiency model was built, based on uniform design (UD) and multiple regression analysis (MRA), and subsequently verified via experiments. The results revealed that the structural parameters have significant influence on the dust collection performance. The suction-inlet diameter, front baffle inclination angle, and suction-inlet inclination angle exerted the highest, second-highest, and lowest influence, respectively. Furthermore, the interaction among structural parameters also influenced the collection performance. The highest, second-highest, and lowest levels of influence were determined for the inlet diameter/baffle inclination angle, inlet inclination angle/baffle inclination angle, and inlet diameter/inlet inclination interactions, respectively. The highest dust collection efficiency (i.e., 96.10%) and a short average detention time of particles in the chamber were realized under the following conditions: suction-inlet diameter and inclination angle: 200 mm and 110°, respectively, and front baffle inclination angle: 105°.
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Kablitz, Stephan, Jörg Bergner, Dietmar K. Hennecke, Manfred Beversdorff, and Richard Schodl. "Darmstadt Rotor No. 2, III: Experimental Analysis of an Aft-Swept Axial Transonic Compressor Stage." International Journal of Rotating Machinery 9, no. 6 (2003): 393–402. http://dx.doi.org/10.1155/s1023621x0300037x.

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At Darmstadt University of Technology (Darmstadt, Germany), the Department of Gas Turbines and Flight Propulsion operates a single-stage transonic compressor test stand. Its main purpose is to provide a database for the validation of computational fluid dynamics codes. In addition, it serves as a testbed for new materials and also for the development of new measurement techniques. After setting up the test rig with a baseline rotor (Rotor No. 1), a titanium bladed disk with conventional radially stacked blade sections, a new rotor (Rotor No. 2) was designed, with the addition of considerable amounts of aft sweep and backward lean. The new rotor's flow field and mechanical properties were investigated by using various measurement techniques, including a laser-2-focus setup.
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Walsh, Glen, Marco Berchiolli, Gregory Guarda, and Apostolos Pesyridis. "Turbocharger Axial Turbines for High Transient Response, Part 1: A Preliminary Design Methodology." Applied Sciences 9, no. 5 (2019): 838. http://dx.doi.org/10.3390/app9050838.

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This paper proposes a preliminary design algorithm for application of a turbocharger axial turbine, based on turbine thermodynamic analysis and the Ainley-Mathieson performance model that converges to the optimal design based on a set of input parameters and engine boundary conditions. A design space sweep was conducted, and a preliminary design was generated with a predicted total to static efficiency of 74.94%. CFD (computational fluid dynamics) was used to successfully validate the algorithm and show the preliminary design had a total to static efficiency of 73.98%. The design also produces the required power to support steady-state operation of the compressor in both free flow conditions and with a constrained pressure outlet.
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Salari, Mohammad Sadegh, Behzad Zarif Boushehri, and Mehrdad Boroushaki. "Aerodynamic analysis of backward swept in HAWT rotor blades using CFD." International Journal of Renewable Energy Development 7, no. 3 (2018): 241–49. http://dx.doi.org/10.14710/ijred.7.3.241-249.

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The aerodynamical design of backward swept for a horizontal axis wind turbine blade has been carried out to produce more power at higher wind velocities. The backward sweep is added by tilting the blade toward the air flow direction. Computational Fluid Dynamics (CFD) calculations were used for solving the conservation equations in one outer stationary reference frame and one inner rotating reference frame, where the blades and grids were fixed in reference to the rotating frame. The blade structure was validated using Reynolds Averaged Navier-Stokes (RANS) solver in a test case by the National Renewable Energy Laboratory (NREL) VI blades results. Simulation results show considerable agreement with the NREL measurements. Standard K-ε turbulence model was chosen for simulations and for the backward swept design process. A sample backward sweep design was applied to the blades of a Horizontal Axis Wind Turbine (HAWT) rotor, and it is obtained that although at the lower wind velocities the output power and the axial thrust of the rotor decrease, at the higher wind velocities the output power increases while the axial thrust decreases. The swept blades have shown about 30 percent increase in output power and about 12 percent decrease in thrust at the wind speed of 14 m/s.Article History: Received June 23rd 2018; Received in revised form Sept 16th 2018; Accepted October 1st 2018; Available onlineHow to Cite This Article: Salari, M.S., Boushehri, B.Z. and Boroushaki, M. (2018). Aerodynamic Analysis of Backward Swept in HAWT Rotor Blades Using CFD. International Journal of Renewable Energy Development, 7(3), 241-249.http://dx.doi.org/10.14710/ijred.7.3.241-249
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Kaparos, Pavlos, Charalampos Papadopoulos, and Kyros Yakinthos. "Conceptual design methodology of a box wing aircraft: A novel commercial airliner." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 14 (2018): 2651–62. http://dx.doi.org/10.1177/0954410018795815.

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In this work, the development of a conceptual design methodology of an innovative aircraft configuration, known as box wing, is presented. A box wing aircraft is based on a continuous-surface nonplanar wing formation with no wing-tips. The A320 medium range conventional cantilever wing aircraft is used as both the reference aircraft and the main competitor of the box wing aircraft. Based on the A320 characteristics and dimensions, a complete aerodynamic analysis of the box wing configuration is made by means of layout design and computational fluid dynamics studies, highlighting the aerodynamic and operating advantages of the box wing configuration compared to the A320 aircraft. The aspect ratio and the Oswald factor of a box wing aircraft differ significantly from the corresponding ones of A320 and provide increased aerodynamic performance. The increased aerodynamic performance leads by consequence, to lower fuel consumption, thus allowing longer range for the same payload or greater payload for the same range, contributing to the efforts for greener environment. In this work, the design methodology begins by estimating the critical initial design parameters, such as aspect ratio, dihedral angle, sweep angle, and taper ratio, which are continuously refined via an iterative process based on a conceptual design study. Various flying scenarios are studied using computational fluid dynamics and analytical calculations, in order to compare the performance of the box wing and the conventional A320, having always the same mission and payload conditions. The conceptual results show that the novel box wing configuration has considerable aerodynamic performance advantages compared to the conventional A320 aircraft.
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Chang, I.-Chung, Thomas R. Norman, and Ethan A. Romander. "Airloads Correlation of the UH-60A Rotor inside the 40- by 80-Foot Wind Tunnel." International Journal of Aerospace Engineering 2014 (2014): 1–19. http://dx.doi.org/10.1155/2014/473989.

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The presented research validates the capability of a loosely coupled computational fluid dynamics (CFD) and comprehensive rotorcraft analysis (CRA) code to calculate the flowfield around a rotor and test stand mounted inside a wind tunnel. The CFD/CRA predictions for the Full-Scale UH-60A Airloads Rotor inside the National Full-Scale Aerodynamics Complex (NFAC) 40- by 80-Foot Wind Tunnel at NASA Ames Research Center are compared with the latest measured airloads and performance data. The studied conditions include a speed sweep at constant lift up to an advance ratio of 0.4 and a thrust sweep at constant speed up to and including stall. For the speed sweep, wind tunnel modeling becomes important at advance ratios greater than 0.37 and test stand modeling becomes increasingly important as the advance ratio increases. For the thrust sweep, both the wind tunnel and test stand modeling become important as the rotor approaches stall. Despite the beneficial effects of modeling the wind tunnel and test stand, the new models do not completely resolve the current airload discrepancies between prediction and experiment.
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Kanchan, Mithun, and Ranjith Maniyeri. "Numerical simulation of buckling and asymmetric behavior of flexible filament using temporal second-order immersed boundary method." International Journal of Numerical Methods for Heat & Fluid Flow 30, no. 3 (2019): 1047–95. http://dx.doi.org/10.1108/hff-06-2019-0467.

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Purpose The purpose of this paper is to perform two-dimensional numerical simulation involving fluid-structure interaction of flexible filament. The filament is tethered to the bottom of a rectangular channel with oscillating fluid flow inlet conditions at low Reynolds number. The simulations are performed using a temporal second-order finite volume-based immersed boundary method (IBM). Further, to understand the relation between different aspect ratios i.e. ratio of filament length to channel height (Len/H) and fixed channel geometry ratio, i.e. ratio of channel height to channel length (H/Lc) on mixing and pumping capabilities. Design/methodology/approach The discretization of governing continuity and Navier–Stokes equation is done by finite-volume method on a staggered Cartesian grid. SIMPLE algorithm is used to solve fluid velocity and pressure terms. Two cases of oscillatory flow conditions are used with the flexible filament tethered at the center of bottom channel wall. The first case is sinusoidal oscillatory flow with phase shift (SOFPS) and second case is sinusoidal oscillatory flow without phase shift (SOF). The simulation results are validated with filament dynamics studies of previous researchers. Further, parametric analysis is carried to study the effect of filament length (aspect ratio), filament bending rigidity and Reynolds number on the complex deformation and behavior of flexible filament interacting with nearby oscillating fluid motion. Findings It is found that selection of right filament length and bending rigidity is crucial for fluid mixing scenarios. The phase shift in fluid motion is also found to critically effect filament displacement dynamics, especially for rigid filaments. Aspect ratio, suitable for mixing applications is dependent on channel geometry ratio. Symmetric deformation is observed for filaments subjected to SOFPS condition irrespective of bending rigidity, whereas medium and low rigidity filaments placed in SOF condition show severe asymmetric behavior. Two key findings of this study are: symmetric filament conformity without appreciable bending produces sweeping motion in fluid flow, which is highly suited for mixing application; and asymmetric behavior shown by the filament depicts antiplectic metachronism commonly found in beating cilia. As a result, it is possible to pin point the type of fluid motion governing fluid mixing and fluid pumping. The developed computational model can, thus, successfully demonstrate filament-fluid interaction for a wide variety of similar problems. Originality/value The present study uses a temporal second-order finite volume-based IBM to examine flexible filament dynamics for various applications such as fluid mixing. Also, it highlights the relationship between channel geometry ratio and filament aspect ratio and its effect on filament sweep patterns. The study further reports the effect of filament displacement dynamics with or without phase shift for inlet oscillating fluid flow condition.
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Dissertations / Theses on the topic "Computational fluid dynamics analysis of a sweeper"

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Aygun, Buket. "Conceptual Design And Analysis Of An Industrial Type Vacuum Sweeper." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/2/12610438/index.pdf.

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In this thesis, design and development and manufacturing processes of an industrial type vacuum sweeper is presented. Thesis is financially supported by Ministry of Industry and Trade-Turkey and M&uuml<br>san A.S. (Makina &Uuml<br>retim Sanayi ve Ticaret A.S.) under SAN-TEZ project number 00028.STZ.2007-1. It is aimed to make innovative design changes and developments on the M&uuml<br>san VSM 060 type vacuum sweeper. To achieve this aim, alternative configuration designs are prepared by using commercial 3D modeling program, Catia&trade<br>V5. Basic vehicle structure is constructed. New M&uuml<br>san VSM 060 will be a fully electrically driven vehicle. All subsystems will be activated by using electrical motors whose power is supplied by batteries. All subsystems are mounted on the chassis which is a welded frame structure made up of 60x40x2 St37-2 grade steel tubes. Finite element analysis (FEA) of the chassis is performed by using commercial structural finite element analysis tools MSC Patran pre and post processor and MSC Nastran solver. Moment calculations are done for structural parts. Cleaning system of the new VSM 060 vehicle is decided to be a combination of mechanical and vacuum cleaning systems. An elevator system will be integrated in addition to vacuum system to pick up coarse particles. The vacuum system will mainly be utilized for very small size particle collection. Computational fluid dynamics (CFD) analyses are done by Punto M&uuml<br>hendislik Ltd. Sti. for the whole cleaning system components by using CFdesign, an upfront CFD analysis tool.
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Baldovin, Brandon James. "Sweep and Taper Analysis of Surfboard Fins Using Computational Fluid Dynamics." DigitalCommons@CalPoly, 2019. https://digitalcommons.calpoly.edu/theses/1983.

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The research presented here provides a basis for understanding the hydrodynamics of surfboard fin geometries. While there have been select studies on fins there has been little correlation to the shape of the fin and its corresponding hydrodynamic performance. This research analyzes how changing the planform shape of a surfboard fin effects its performance and flow field. This was done by isolating the taper and sweep distribution of a baseline geometry and varying each parameter individually whilst maintaining a constant span and surface area. The baseline surfboard fin was used as a template in Matlab to generate a set of x and y coordinates that defined the outline of the fin shape. These coordinates were then altered by changing either the sweep or taper distribution and resulted in new, unique planform shapes. The new shapes were used to generate 3D models with the NACA 0006 foil as the cross-section hydrofoil. After the geometry was modeled, each fin was meshed and simulated in CFD for incidence angles ranging from 0o to 20o and a fin Reynolds Number of 3.51x105. When the sweep distribution was changed, there was a direct correlation to vortex formation off the leading edge. Increasing the sweep generated a stronger vortex that persisted for higher angles of attack and resulted in higher moments but increased drag. Changing the taper distribution was not as influential. The tapered fin set showed similar flow fields and body forces to each other. Making a fin more rectangular had slight decreases in drag but made the shape more prone to separation.
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Sahin, Emre. "Conceptual Design, Testing And Manufacturing Of An Industrial Type Electro-hydraulic Vacuum Sweeper." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613747/index.pdf.

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CONCEPTUAL DESIGN, TESTING AND MANUFACTURING OF AN INDUSTRIAL TYPE ELECTRO-HYDRAULIC VACUUM SWEEPER SAHIN, Emre M.Sc., Department of Mechanical Engineering Supervisor : Prof. Dr. Kahraman ALBAYRAK Co-Supervisor: Prof. Dr. Bilgin KAFTANOGLU September 2011, 156 pages In this thesis, conceptual design, testing, development and manufacturing processes of the cleaning (elevator and fan system) and electro-hydraulic systems of an industrial type vacuum sweeper are presented. Thesis is financially supported by Ministry of Science, Industry and Technology (Turkey) and M&uuml<br>san A.S. (Makina &Uuml<br>retim Sanayi ve Ticaret A.S.) under the SAN-TEZ projects with numbers 00028.STZ.2007-1 and 00623.STZ.2010-1. The main purpose is to make critical design changes on existing fan system, designing a new elevator system and eventually obtaining efficient and powerful cleaning system. For design, Catia and SolidWorks softwares are used. Within the SAN-TEZ project, all CFD solutions were provided by Punto Engineering. Unlike many industrial type vacuum sweepers, new design will be electrically and electro-hydraulic controlled. All cleaning system of new &lsquo<br>M&Uuml<br>SAN Vacuum Sweeper&rsquo<br>will be activated by using hydraulic motors (traction system including hydraulic system is driven by the brushless DC electric motor as well) and the power of all these systems is supplied by batteries which are placed in the middle of the vehicle. Elevator and fan system can be considered as a group for a street sweeper for cleaning operations. Fan and elevator systems both gain an important place especially in cleaning operations due to lifting heavy and small particles from the ground. Fan system is used for sucking the small materials and dust by vacuum and elevator system is used to elevate heavier materials such stones, bottles, cans. Therefore, it is essential to design an efficient and powerful fan and elevator system for a street sweeper. The thesis work includes the design, development, supervision of manufacturing, simulation and testing of the cleaning (elevator and fan systems) and electro-hydraulic system of the street cleaners.
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Demir, H. Ozgur. "Computational Fluid Dynamics Analysis Of Store Separation." Master's thesis, METU, 2004. http://etd.lib.metu.edu.tr/upload/12605294/index.pdf.

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In this thesis, store separation from two different configurations are solved using computational methods. Two different commercially available CFD codes<br>CFD-FASTRAN, an implicit Euler solver, and an unsteady panel method solver USAERO, coupled with integral boundary layer solution procedure are used for the present computations. The computational trajectory results are validated against the available experimental data of a generic wing-pylon-store configuration at Mach 0.95. Major trends of the separation are captured. Same configuration is used for the comparison of unsteady panel method with Euler solution at Mach 0.3 and 0.6. Major trends are similar to each other while some differences in lateral and longitudinal displacements are observed. Trajectories of a fueltank separated from an F-16 fighter aircraft wing and full aircraft configurations are found at Mach 0.3 using only the unsteady panel code. The results indicate that the effect of fuselage is to decrease the drag and to increase the side forces acting on the separating fueltank from the aircraft. It is also observed that the yawing and rolling directions of the separating fueltank are reversed when it is separated from the full aircraft configuration when compared to the separation from the wing alone configuration.
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Williams, Adam N. "Computational fluid dynamics analysis of a dual mode thruster." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA370896.

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Thesis (M.S. in Astronautical Engineering) Naval Postgraduate School, September 1999.<br>"September 1999". Thesis advisor(s): Garth V. Hobson. Includes bibliographical references (p. 135-136). Also Available online.
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Tsang, Chang Ming. "Analysis of pleated air filters using computational fluid dynamics." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp03/MQ29434.pdf.

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Monahan, Sarah Marie. "Computational fluid dynamics analysis of air-water bubble columns." [Ames, Iowa : Iowa State University], 2007.

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Gilmore, Jordan David. "Computational Fluid Dynamics Analysis of Jet Engine Test Facilities." Thesis, University of Canterbury. Mechanical Engineering, 2012. http://hdl.handle.net/10092/7238.

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This thesis investigates the application of CFD techniques to the aerodynamic analysis of a U-shaped JETC. Investigations were carried out to determine the flow patterns present at a number of locations within the structure of a full U-shaped JETC. The CFD solutions produced in these investigations used recommendations from the literature in the set-up of the CFD solver, and provided the computational component towards problem-specific validation of the CFD techniques used. A structured series of CFD-aided investigation and design processes were then performed. These processes were based around a series of analyses that evaluated the influence of a number of cell parameters in terms of cell airflow efficiency and velocity distortion. Four cell components; the inlet and exhaust stack baffle arrangements, the turning-vanes, the rear of the working section and augmenter entrance, and the lower exhaust stack, including the BB, were investigated in individual analyses. Throughout the investigations the value of CFD as a design tool was constantly assessed. Overall, the findings suggest that aerodynamic optimisation of the baffle arrangements would provide the greatest gains to cell airflow efficiency. As some cells contain as many as three baffle arrangements, the potential increases made to cell airflow capacity are sizable. Through implementing the findings of the baffle arrangement investigations, static pressure loss across the five-row baseline arrangement was reduced by 79%. For low levels of velocity distortion in the upstream region of the working section, the need to design the inlet stack baffles in the turning-vane arrangement was highlighted. Mid-baffle vane alignment, consistent flow channels, and sufficiently low chord to gap ratios should be incorporated into a turning-vane design to maximise flow uniformity. The need for the baffle and vane components to combine with the geometry of the cell to limit adverse pressure gradients was found as a requirement to minimise inner corner separation, and the downstream threat it creates to a safe testing environment. CFD proved to be a valuable analysis tool throughout the investigations performed in this thesis. The number of design iterations analysed, and the detail of data that could be extracted, significantly exceeded what could have been achieved through an isolated experimental testing programme.
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Del, Toro Adam. "Computational Fluid Dynamics Analysis of Butterfly Valve Performance Factors." DigitalCommons@USU, 2012. https://digitalcommons.usu.edu/etd/1456.

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Butterfly valves are commonly used in industrial applications to control the internal flow of both compressible and incompressible fluids. A butterfly valve typically consists of a metal disc formed around a central shaft, which acts as its axis of rotation. As the valve's opening angle is increased from 0 degrees (fully closed) to 90 degrees (fully open), fluid is able to more readily flow past the valve. Characterizing a valve's performance factors, such as pressure drop, hydrodynamic torque, flow coefficient, loss coefficient, and torque coefficient, is necessary for fluid system designers to account for system requirements to properly operate the valve and prevent permanent damage from occurring. This comparison study of a 48-inch butterfly valve's experimental performance factors using Computational Fluid Dynamics (CFD) in an incompressible fluid at Reynolds numbers ranging approximately between 105 to 106 found that for mid-open positions (30-60 degrees), CFD was able to appropriately predict common performance factors for butterfly valves. For lower valve angle cases (10-20 degrees), CFD simulations failed to predict those same values, while higher valve angles (70-90 degrees) gave mixed results. (152 pages)
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Perez, Rafael A. "Uncertainty Analysis of Computational Fluid Dynamics Via Polynomial Chaos." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/28984.

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The main limitations in performing uncertainty analysis of CFD models using conventional methods are associated with cost and effort. For these reasons, there is a need for the development and implementation of efficient stochastic CFD tools for performing uncertainty analysis. One of the main contributions of this research is the development and implementation of Intrusive and Non-Intrusive methods using polynomial chaos for uncertainty representation and propagation. In addition, a methodology was developed to address and quantify turbulence model uncertainty. In this methodology, a complex perturbation is applied to the incoming turbulence and closure coefficients of a turbulence model to obtain the sensitivity derivatives, which are used in concert with the polynomial chaos method for uncertainty propagation of the turbulence model outputs.<br>Ph. D.
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Books on the topic "Computational fluid dynamics analysis of a sweeper"

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Computational fluid dynamics. Chapman and Hall/CRC, 2011.

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Wendt, John F. Computational Fluid Dynamics. Springer Berlin Heidelberg, 2009.

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T, Chiang Steve, ed. Computational fluid dynamics for engineers. Engineering Education System, 1993.

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Computational fluid dynamics for engineers. Engineering Education System, 1989.

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Hunter, L. G. Inlet analysis using computational fluid dynamics. AIAA, 1986.

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Computational techniques for fluid dynamics. 2nd ed. Springer-Verlag, 1991.

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Fletcher, Clive. Computational techniques for fluid dynamics. Springer-Verlag, 1988.

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Fletcher, Clive. Computational techniques for fluid dynamics. Springer-Verlag, 1988.

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Murphy, Alyssa D. Computational fluid dynamics: Theory, analysis, and applications. Nova Science Publishers, 2011.

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Computational fluid mechanics: Selected papers. Academic Press, 1989.

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Book chapters on the topic "Computational fluid dynamics analysis of a sweeper"

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Horritt, M. S. "Parameterisation, Validation and Uncertainty Analysis of CFD Models of Fluvial and Flood Hydraulics in the Natural Environment." In Computational Fluid Dynamics. John Wiley & Sons, Ltd, 2005. http://dx.doi.org/10.1002/0470015195.ch9.

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Schaefer, Philip, Markus Gampert, Jens Henrik Goebbert, and Norbert Peters. "Dissipation Element Analysis of Inhomogenous Turbulence." In Computational Fluid Dynamics 2010. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17884-9_91.

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Rumpfkeil, Markus P., Wataru Yamazaki, and Dimitri J. Mavriplis. "Uncertainty Analysis Utilizing Gradient and Hessian Information." In Computational Fluid Dynamics 2010. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17884-9_32.

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Mesbah, M., W. Desmet, and M. Baelmans. "URANS Analysis of Flow-Induced Cavity Resonances." In Computational Fluid Dynamics 2006. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-92779-2_78.

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Fletcher, Clive A. J. "Symbolic Analysis and Computational Algorithm Construction." In Advances in Fluid Dynamics. Springer New York, 1989. http://dx.doi.org/10.1007/978-1-4612-3684-9_6.

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Kiris, Cetin, William Chan, Dochan Kwak, and Jeffrey Housman. "Time-Accurate Computational Analysis of the Flame Trench." In Computational Fluid Dynamics 2008. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01273-0_31.

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Ooba, Yoshinori, Hidekazu Kodama, Yoshiya Nakamura, et al. "Large Eddy Simulation Analysis of Lobed Mixer Nozzle." In Computational Fluid Dynamics 2000. Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-642-56535-9_66.

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Swanson, R. C., E. Turkel, and S. Yaniv. "Analysis of a RK/Implicit Smoother for Multigrid." In Computational Fluid Dynamics 2010. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17884-9_51.

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Kikuchi, Dai, and Mingyu Sun. "Numerical Analysis of Optical Systems for Compressible Flow Visualization." In Computational Fluid Dynamics 2008. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01273-0_109.

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Husain, Afzal, and Kwang-Yong Kim. "Optimization of Ribbed Microchannel Heat Sink Using Surrogate Analysis." In Computational Fluid Dynamics 2008. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01273-0_69.

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Conference papers on the topic "Computational fluid dynamics analysis of a sweeper"

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Daly, John, Elvis Sheik Bajeet, Ajit Thakker, and Patrick Frawley. "A 3D Computational Fluid Dynamics Analysis of the Wells Turbine." In ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/fedsm2002-31321.

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This paper deals with the application of Computational Fluid Dynamics (CFD) to the performance comparison of some proposed blade designs for the Well’s Turbine. The turbines were modelled at typical Reynolds numbers for full scale rigs and the results were found to correlate well with scale predictions from experimental data. Three different turbine designs were analysed, one a 4-bladed rotor and the other two 8-bladed rotors. The only difference between the two 8-bladed rotors was the addition of forward sweep to one. The addition of forward sweep was shown to have little effect on the overall performance of the 8-bladed rotor. The 4-bladed rotor was shown to have the highest efficiency and pressure drop at low flow rates, however it was also shown to have a much smaller operating range than the 8-bladed rotors.
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Chen, Xiaoxuan, Mingyang Yang, Kangyao Deng, and Yunlong Bai. "Numerical Analysis of a Centrifugal Fan for a Road Sweeper." In ASME 2017 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/fedsm2017-69103.

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Road sweeper is the widely-employed machine to clear up garbage and dust on streets. Its performance has profound influence on the reduction of fuel consumption and hence CO2 emission. The key component of a road sweeper is a centrifugal fan which produces suction force for clearing. Therefore, the performance of this device has direct impact on fuel economy of the machine. This paper targets at the performance analysis of a centrifugal fan in a commercial road sweeper. Firstly, the performance and flow field of the centrifugal fan are analyzed by computational fluid dynamics (CFD) method. The breakdown of the flow loss in the fan shows that the volute and the impeller are major components contributing to flow loss in the fan. The flow at the inlet of the impeller is highly distorted due the interaction among the asymmetrical inlet duct, the leakage and the volute tongue. Because of the interaction, flow passages near the tongue are the ones with the highest flow loss. Moreover, the flow velocity entering the volute is considerably high which thus results in high flow loss in the volute. Finally, based on the flow field analysis, an inlet duct with round shape is designed preliminarily and simulated together with the centrifugal fan. The results show that the efficiency can be improved by more than 4% compared with the original configuration due to the alleviation of the interaction.
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Yamamoto, Yukimitsu, Yasuhiro Wada, and Minako Yoshioka. "HYFLEX computational fluid dynamics analysis. II." In Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2274.

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Milholen, am E, I, William, and Ndaona IChokani. "Computational analysis of semi-span test techniques." In Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2290.

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Menon, Karthik, and Rajat Mittal. "Computational Modelling and Analysis of Aeroelastic Flutter." In 2018 Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3080.

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HUNTER, L., and T. KENT. "Inlet analysis using computational fluid dynamics." In Aircraft Systems, Design and Technology Meeting. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-2661.

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TAYLOR, III, ARTHUR, VAMSHI KORIVI, and GENE HOU. "Approximate analysis and sensitivity analysis methods for viscous flow involving variation of geometric shape." In 10th Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1569.

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Gammacurta, Eric, Dominique Pelletier, Stéphane Etienne, and F. Ilinca. "Sensitivity Analysis of Unsteady RANS Flows." In 19th AIAA Computational Fluid Dynamics. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-4269.

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Kunz, R., W. Cope, S. Venkateswaran, R. Kunz, W. Cope, and S. Venkateswaran. "Stability analysis of implicit multi-fluid schemes." In 13th Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2080.

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COSNER, RAYMOND, and AUGUST VERHOFF. "Aeropropulsion analysis of tactical aircraft - Status and plans." In 10th Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1528.

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Reports on the topic "Computational fluid dynamics analysis of a sweeper"

1

Beach, Robert, Duncan Prahl, and Rich Lange. Computational Fluid Dynamics Analysis of Flexible Duct Junction Box Design. Office of Scientific and Technical Information (OSTI), 2013. http://dx.doi.org/10.2172/1117056.

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Coleman, Hugh W. Incorporation of Uncertainty Analysis in Experimental/Computational Fluid Dynamics Validations. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada401059.

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Beach, Robert, Duncan Prahl, and Rich Lange. Computational Fluid Dynamics Analysis of Flexible Duct Junction Box Design. Office of Scientific and Technical Information (OSTI), 2013. http://dx.doi.org/10.2172/1220913.

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Chandramouli, Deepthi, Mehrdad Shahnam, and William Rogers. Computational Fluid Dynamics Analysis of a 12 MW Circulating Fluidized Bed Rise. Office of Scientific and Technical Information (OSTI), 2020. http://dx.doi.org/10.2172/1673607.

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HABCHI, S. D., S. G. Rock, G. S. Hufford, V. J. Parsatharsay, and A. J. Przekwas. Computational Fluid Dynamics Tools for Escape Systems Aerodynamic Analysis. Volume 2 of 2. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada353755.

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HABCHI, S. D., S. G. Rock, G. S. Hufford, V. J. Parsatharsay, and A. J. Przekwas. Computational Fluid Dynamics Tools for Escape Systems Aerodynamic Analysis. Volume 1 of 2. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada353756.

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Sakagawa, Keiji, Hideto Yoshitake, and Eiji Ihara. Computational Fluid Dynamics for Design of Motorcycles (Numerical Analysis of Coolant Flow and Aerodynamics). SAE International, 2005. http://dx.doi.org/10.4271/2005-32-0033.

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Heavy, Karen R., Jubaraj Sahu, and Stephen A. Wilkerson. A Multidisciplinary Coupled Computational Fluid Dynamics (CFD) and Structural Dynamics (SD) Analysis of a 2.75-in Rocket Launcher. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada402247.

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Nickolaus, D. Computational Fluid Dynamics (CFD) Analysis and Development of Halon-Replacement Fire Extinguishing Systems (Phase 2). Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada585794.

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Douglas, Craig C., and Adam F. Zornes. Computational Fluid Dynamics (CFD) Modeling And Analysis Delivery Order 0006: Cache-Aware Air Vehicles Unstructured Solver (AVUS). Defense Technical Information Center, 2005. http://dx.doi.org/10.21236/ada451530.

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