Relevant bibliographies by topics / Fluid- and Aerodynamics

Contents

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

Academic literature on the topic 'Fluid- and Aerodynamics'

Author: Grafiati
Published: 4 June 2021
Last updated: 30 July 2024

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Journal articles on the topic "Fluid- and Aerodynamics"

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Wang, Jianfeng, Hao Li, Yiqun Liu, Tao Liu, and Haibo Gao. "Aerodynamic research of a racing car based on wind tunnel test and computational fluid dynamics." MATEC Web of Conferences 153 (2018): 04011. http://dx.doi.org/10.1051/matecconf/201815304011.

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Wind tunnel test and computational fluid dynamics (CFD) simulation are two main methods for the study of automotive aerodynamics. CFD simulation software solves the results in calculation by using the basic theory of aerodynamic. Calculation will inevitably lead to bias, and the wind tunnel test can effectively simulate the real driving condition, which is the most effective aerodynamics research method. This paper researches the aerodynamic characteristics of the wing of a racing car. Aerodynamic model of a racing car is established. Wind tunnel test is carried out and compared with the simulation results of computational fluid dynamics. The deviation of the two methods is small, and the accuracy of computational fluid dynamics simulation is verified. By means of CFD software simulation, the coefficients of six aerodynamic forces are fitted and the aerodynamic equations are obtained. Finally, the aerodynamic forces and torques of the racing car travel in bend are calculated.
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Hong, Sungchan, Takeshi Asai, and Byung Mook Weon. "Surface Patterns for Drag Modification in Volleyballs." Applied Sciences 9, no. 19 (September 25, 2019): 4007. http://dx.doi.org/10.3390/app9194007.

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Surface patterns on objects are important in aerodynamics. We show how surface patterns on volleyballs modify their aerodynamic performances. Conventional volleyballs with six panels show different aerodynamic characteristics along transverse and diagonal directions. Interestingly, isotropic surface patterning with hexagons or dimples enables us to achieve isotropic aerodynamics. This result gives insight into surface-mediated flight controls of projectiles through resisting fluid media.
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Deng, Yong Quan, Tian Li, Yi Sheng Zou, Ji Ye Zhang, and Wei Hua Zhang. "Equilibrium Characteristics of High-Speed Train in Crosswind." Applied Mechanics and Materials 275-277 (January 2013): 532–36. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.532.

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A fast approach to high-speed train co-simulation between aerodynamics and train-track coupling dynamics is presented. With this method, the fluid-structure dynamic performances of a high-speed train are simulated with different crosswind velocity and train velocity. The aerodynamic forces and train dynamics are compared under off-line simulation and equilibrium state method. Considering the fluid-structure interaction, there is significant influence on the head aerodynamics and train dynamics. The results show that it is necessary to consider changing attitude in crosswind
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Danehy, Paul M., Ross A. Burns, Daniel T. Reese, Jonathan E. Retter, and Sean P. Kearney. "FLEET Velocimetry for Aerodynamics." Annual Review of Fluid Mechanics 54, no. 1 (January 5, 2022): 525–53. http://dx.doi.org/10.1146/annurev-fluid-032321-025544.

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Long-lasting emission from femtosecond excitation of nitrogen-based flows shows promise as a useful mechanism for a molecular tagging velocimetry instrument. The technique, known as femtosecond laser electronic excitation tagging (FLEET), was invented at Princeton a decade ago and has quickly been adopted and used in a variety of high-speed ground test flow facilities. The short temporal scales offered by femtosecond amplifiers permit nonresonant multiphoton excitation, dissociation, and weak ionization of a gaseous medium near the beam's focus without the generation of a laser spark observed with nanosecond systems. Gated, intensified imaging of the resulting emission enables the tracking of tagged molecules, thereby measuring one to three components of velocity. Effects of local heating and acoustic disturbances can be mitigated with the selection of a shorter-wavelength excitation source. This review surveys the development of FLEET over the decade since its inception, as it has been implemented in several test facilities to make accurate, precise, and seedless velocimetry measurements for studying complex high-speed flows.
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Choi, Haecheon, Jungil Lee, and Hyungmin Park. "Aerodynamics of Heavy Vehicles." Annual Review of Fluid Mechanics 46, no. 1 (January 3, 2014): 441–68. http://dx.doi.org/10.1146/annurev-fluid-011212-140616.

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Jo, Bruce W., and Tuba Majid. "Aerodynamic Analysis of Camber Morphing Airfoils in Transition via Computational Fluid Dynamics." Biomimetics 7, no. 2 (April 22, 2022): 52. http://dx.doi.org/10.3390/biomimetics7020052.

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In this paper, the authors analyze an important but overlooked area, the aerodynamics of the variable camber morphing wing in transition, where 6% camber changes from 2% to 8% using the two airfoil configurations: NACA2410 and NACA8410. Many morphing works focus on analyzing the aerodynamics of a particular airfoil geometry or already morphed case. The authors mainly address "transitional" or "in-between" aerodynamics to understand the semantics of morphing in-flight and explore the linearity in the relationship when the camber rate is gradually changed. In general, morphing technologies are considered a new paradigm for next-generation aircraft designs with highly agile flight and control and a multidisciplinary optimal design process that enables aircraft to perform substantially better than current ones. Morphing aircraft adjust wing shapes conformally, promoting an enlarged flight envelope, enhanced performance, and higher energy sustainability. Whereas the recent advancement in manufacturing and material processing, composite and Smart materials has enabled the implementation of morphing wings, designing a morphing wing aircraft is more challenging than modern aircraft in terms of reliable numerical modeling and aerodynamic analysis. Hence, it is interesting to investigate modeling the transitional aerodynamics of morphing airfoils using a numerical analysis such as computational fluid dynamics. The result shows that the SST k-ω model with transition/curvature correction computes a reasonably accurate value than an analytical solution. Additionally, the CL is less sensitive to transition near the leading edge in airfoils. Therefore, as the camber rate changes or gradually increases, the aerodynamic behavior correspondingly changes linearly.
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Metar, Manas. "Aerodynamic Analysis of Spoiler at Varying Speeds and Angles." International Journal for Research in Applied Science and Engineering Technology 9, no. 11 (November 30, 2021): 526–35. http://dx.doi.org/10.22214/ijraset.2021.38843.

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Abstract: Spoilers have been there in practice since years for the purpose of improving aerodynamics of a car. The pressure drag created at the end of the vehicle, referred to as wake region affects handling of the vehicle. This could be hazardous for the cars at high speeds. By adding a spoiler to the rear of the car reduces that pressure drag and the enhanced downforce helps in better traction. The paper presents aerodynamic analysis of a spoiler through Computational Fluid Dynamics analysis. The spoiler is designed using Onshape software and analyzed through SIMSCALE software. The simulation is carried out by changing angles of attack and velocities. The simulation results of downforce and drag are compared on the basis of analytical method. Keywords: Designing a spoiler, Design and analysis of spoiler, Aerodynamics of spoiler, Aerodynamic analysis of spoiler, Computational fluid dynamics, CFD analysis, CFD analysis of spoiler, Spoiler at variable angles, Types of spoilers, Analytical aerodynamic analysis.
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Xie, Meng, and Xiaoyan Liu. "The influence and application of nonlinear aerodynamics on static derivatives in transonic regime." Journal of Physics: Conference Series 2512, no. 1 (May 1, 2023): 012007. http://dx.doi.org/10.1088/1742-6596/2512/1/012007.

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Abstract This paper details two static aeroelastic analysis methods applied to a passenger aircraft model with high aspect ratio wing. The influence of nonlinear aerodynamic force on static aeroelastic derivatives in the transonic regime is analysed. The traditional aerodynamic influence coefficient (AIC) matrix method can produce fast and reliable aerodynamic force and is widely used in aeroelastic analysis. However, the AIC matrix computed by linear aerodynamics will lead to some errors in transonic regime because of the nonlinear effect of aerodynamics. By generating the correction matrices, the AIC matrix is modified, and the accuracy of transonic static aeroelastic correction of aerodynamic data can be improved. The static derivatives are compared to the results of the computational fluid dynamics (CFD) / computational structural (CSD) interaction method.
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Fakhruddin, Muhammad, Hangga Wicaksono, Fauzan Baananto, Hilmi Iman Firmansyah, Nurlia Pramita Sari, Mochamad Muzaki, Khelvindra Rizky Akbarsyah D, and Noveri Dwi Hardyanto. "OPTIMASI AERODINAMIKA BODI MOBIL HEMAT ENERGI KEN DEDES ELECTRIC EVO 3 MENGGUNAKAN METODE COMPUTATIONAL FLUID DYNAMICS (CFD)." Eksergi 17, no. 1 (January 24, 2021): 36. http://dx.doi.org/10.32497/eksergi.v17i1.2219.

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Aerodynamics is a branch of science that discusses the movement of an object in the air. Aerodynamics comes from the words aero = air and dynamics = force of motion. The study of air forces is a branch of fluid mechanics. This study is a continuation of the study of hydrodynamics, where the science of the motion of air has a close relationship with other sciences. Physics, mathematics, mechanics, meteorology and others are branches of science that are closely related to aerodynamics. Where in the science of aerodynamics, it discusses the principle of stationary air, specifically about the changes experienced by the air when there is a change in geometry. In this study, CFD analysis was carried out to inspect and optimize the airflow through the energy-efficient car body "Ken dedes Evo 3" Malang State Polytechnic to participate in energy-efficient car competitions by following the regulations and packaging requirements in energy-efficient car contests. The aerodynamic analysis of the energy-efficient car was carried out using the ANSYS simulation software. This aerodynamic research aims to reduce the drag coefficient and lift coefficient of energy-efficient cars. In the end, the energy-efficient car Ken Dedes Electric Evo 3 has an improved drag coefficient of 0.03 and a lift coefficient of 0.034. This is obtained from the simulation only on the car body.
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Barber, T. J., G. Doig, C. Beves, I. Watson, and S. Diasinos. "Synergistic integration of computational fluid dynamics and experimental fluid dynamics for ground effect aerodynamics studies." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, no. 6 (June 2012): 602–19. http://dx.doi.org/10.1177/0954410011414321.

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This article highlights the ‘synergistic’ use of experimental fluid dynamics (EFD) and computational fluid dynamics (CFD), where the two sets of simulations are performed concurrently and by the same researcher. In particular, examples from the area of ground effect aerodynamics are discussed, where the major facility used was also designed through a combination of CFD and EFD. Three examples are than outlined, to demonstrate the insight that can be obtained from the integration of CFD and EFD studies. The case studies are the study of dimple flow (to enhance aerodynamic performance), the analysis of a Formula-style front wing and wheel, and the study of compressible flow ground effect aerodynamics. In many instances, CFD has been used to not only provide complementary information to an experimental study, but to design the experiments. Laser-based, non-intrusive experimental techniques were used to provide an excellent complement to CFD. The large datasets found from both experimental and numerical simulations have required a new methodology to correlate the information; a new post-processing method has been developed, making use of the kriging and co-kriging estimators, to develop correlations between the often disparate data types.
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Dissertations / Theses on the topic "Fluid- and Aerodynamics"

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Barman, Emelie. "Aerodynamics of Flutter." Thesis, KTH, Mekanik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-34152.

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The unsteady ow around an aerofoil placed in a uniform ow stream with an angle of attack is investigated, under the assumption of inviscid, incompressible, two-dimensional flow. In particular, a function of the velocity jump over the wake is achieved, where this function depends on the horizontal displacement and time. The aerofoil geometry is represented by two arbitrary functions, one for the upper and one for the lower side of the aerofoil. These functions are dependent on time, hence the aerofoil can perform oscillating movement, which is the case when subjected to utter. The governing equations for the ow are the Euler equations. By assuming thin aerofoil, small angle of attack and that the perturbation of the wake is small, the problem is linearised. It is shown that the linearised Euler equations can be rewritten as the Cauchy-Riemann equations, and an analytic function exists where its real part is the horizontal velocity component and its imaginary part is the vertical velocity component with opposite sign. The ow eld is then investigated in the complex plane by making an appropriate branch cut removing all discontinuities, and with restrictions on the analytic function such that the kinematic and boundary conditions are satis ed. By using Cauchy's integral formula an expression for the anti-symmetric part of the analytic function is achieved. A general expression for the velocity jump over the wake is obtained, which is applied to the speci c case of harmonic oscillations for a symmetric aerofoil. In the end three types of utter is investigated; twisting oscillations around the centre of stiness, vertical oscillation, and aileron flutter.
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Horton, F. G. "Aerodynamics and heat transfer of turbine blading." Thesis, University of Oxford, 1985. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.375214.

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Peters, Brett. "On Accelerating Road Vehicle Aerodynamics." Thesis, The University of North Carolina at Charlotte, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10791882.

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Road vehicle aerodynamics are primarily focused on developing and modeling performance at steady-state conditions, although this does not fully encompass the entire operating envelope. Considerable vehicle acceleration and deceleration occurs during operation, either because of driver input or from transient weather phenomenon such as wind gusting. With this considered, high performance road vehicles experience body acceleration rates well beyond ±1G to navigate courses during efficient transition in and out of corners, accelerating from maximum straight-line speed to manageable cornering speeds, and then back to maximum straight-line speed. This dissertation aims to answer if longitudinal acceleration is important for road vehicle aerodynamics with the use of transient Computational Fluid Dynamics (CFD) to develop a method for obtaining ensemble averages of forces and flow field variables. This method was developed on a simplified bluff body, a channel mounted square cylinder, achieving acceleration through periodic forcing of far field velocity conditions. Then, the method was applied to an open-source road vehicle geometry, the DrivAer model, and a high performance model which was created for this dissertation, the DrivAer-GrandTouringRacing (GTR) variant, as a test model that generates considerable downforce with low ground proximity. Each test body experienced drag force variations greater than ±10% at the tested velocities and acceleration rates with considerable variations to flow field distributions. Finally, an empirical formulation was used to obtain non-dimensional coefficients for each body from their simulated force data, allowing for force comparison between geometries and modeling of aerodynamic force response to accelerating vehicle conditions.

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Melius, Matthew Scott. "Mechanisms and Identification of Unsteady Separation Development and Remediation." PDXScholar, 2018. https://pdxscholar.library.pdx.edu/open_access_etds/4064.

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Unsteady flow separation represents a highly complex and important area of study within fluid mechanics. The extent of separation and specific time scales over which it occurs are not fully understood and has significant consequences in numerous industrial applications such as helicopters, jet engines, hydroelectric turbines and wind turbines. A direct consequence of unsteady separation is the erratic movement of the separation point which causes highly dynamic and unpredictable loads on an airfoil. Current computational models underestimate the aerodynamic loads due to the inaccurate prediction of the emergence and severity of unsteady flow separation especially in response to a sudden change in the effective angle of attack. To capture the complex flow phenomena over wind turbine blades during stall development, a scaled three-dimensional non-rotating blade model is designed to be dynamically similar to a rotating full-scale NREL 5MW wind turbine blade. A time-resolved particle image velocimetry (PIV) investigation of flow behavior during the stall cycle examines the processes of stall development and flow reattachment. The flow fields are examined through the application of Eulerian techniques such as proper orthogonal decomposition and empirical mode decomposition to capture unsteady separation characteristics within the flow field. Then, for a higher order description, coherent structures such as vortices and material lines are resolved to fully characterize the flow during a full pitching cycle in a Lagrangian framework. The Eulerian and Lagrangian methods described in the present analysis is extended to investigate the spanwise characteristics within the root section of a three dimensional airfoil. Furthermore, statistical information of the separation point is pursued along four spanwise positions during two cases of unsteady separation. The results of the study describe a critical role of surface vorticity accumulation in unsteady separation and reattachment. Evaluation of the unsteady characteristics of the shear layer reveal evidence that the build-up and shedding of surface vorticity directly influence the dynamic changes in separation point. The quantitative characterization of surface vorticity and shear layer stability enables improved aerodynamic design, but also has broader implications on the larger discipline of unsteady fluid dynamics.
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Lejon, Marcus. "Aerodynamic Investigation of Air Inlets on Aircrafts with Application of Computational Fluid Dynamics." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-12820.

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Air inlets in some form are used on all commercial airliners today. The type of air inlet investigated in this report is a NACA inlet submerged into a surface. This surface is within this thesis a test section wall of a wind tunnel. The considered wind tunnel is TWG in Göttingen (Germany) that operates in transonic speeds. Submerged inlets have the main advantage of low aeroynamic drag from the inlet itself. The importance of reducing drag, and the attention given to this subject is increasing as fuel prices rise as well as public awareness of environmental impact by all of us. The outcome of this thesis contributes to the government-funded project ECOCENTS which deals with the design of innovative new aircraft cooling systems and the detailed flow analysis of these systems. This thesis was carried out at the company Airbus in Bremen, Germany. The main objective of this report was the evaluation of the ram pressure efficiency of four different ramp angles of a NACA inlet and the estimation of the drag caused by these geometries with the use of Computational Fluid Dynamics (CFD). The flow solver used was TAU, a Reynolds-Averaged Navier-Stokes (RANS) solver developed by the German Aerospace Center (DLR). The inlet consisted of one ramp section where the ramp angle was fixed at 7 degrees, and a second variable ramp section. The following different angles were investigated: 4, 7, 10 and 15 degrees. These configurations were evaluated at a velocity of Mach 0.8 and a Reynolds number of 10*10^6. The ramp angle of 7 degrees was evaluated at two additional velocities (Mach 0.73 and Mach 0.87) and at two additional Reynolds numbers (5*10^6 and 15*10^6) at Mach 0.8. The inlet efficiency outcome of this study was located between two other investigations. The results of this RANS computation predicted a higher total pressure at the inlet throat plane compared to a previous CFD investigation where a different RANS solver at the same geometry was used. In comparison to an estimation method mainly based on experimental data (ESDU method), the recent study showed a lower total pressure at the inlet throat plane. The aerodynamic drag that arised by the presence of the inlet system was calculated within this thesis to be higher than the outcome of the experimental data based (ESDU) method. The advantage of using a NACA type inlet was observed to be highly related to the ramp angle. Vortices are originated and develop along the edges of the intake ramp walls. These two vortices help to transport higher energy flow from the free stream into the inlet and therefore reduce the boundary layer thickness in the inlet region. For lower mass flows (0.10 - 0.20 kg/s) a ramp angle of 7 degrees was seen to be prefered in view of ram pressure efficiency. At a higher mass flow (0.25 kg/s) the 10 degrees ramp angle was prefered, followed by the 15 degrees ramp angle at the highest investigated mass flows (0.30 - 0.35 kg/s). In view of drag, the lowest ramp angle possible for a given mass flow was seen to be most advantagous. Future work on this subject will include simulation of an inlet in combination with a heat exchanger and a ram air outlet. This arrengement will be the same as in the investigation at the TWG test campaign and therefore comparable. The difference in outcome of the separate CFD analysis was discussed within this investigation but could not be completely cleared.
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Henderson, Jason. "Investigation of cavity flow aerodynamics using computational fluid dynamics." Thesis, University of Glasgow, 2001. http://theses.gla.ac.uk/3483/.

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Open cavity flow is that of most interest to researchers. The flow is typical to that found to exist in the bomb bay of the F-111 and is characterised by intense acoustic levels. A review of the work of previous experimental researchers is included for comparison with the findings of the present thesis. The flow physics indicate that a series of vortices travel downstream in the cavity and are driven by vorticity generated at the upstream lip of the cavity. When strengthened the downstream moving vortex influences the mass addition and expulsion at the trailing edge initiating a pressure wave which propagates upstream and sustains the process of completing the feedback lopp. These features are elucidated upon in the present thesis. The flow at Mach 0.85 and Mach 1.19 is analysed with only differences in the external stream being apparent for the higher Mach number case. The suppression of the acoustic environment is investigated by sloping the aft wall of the cavity. The results of the CFD study are used to examine why sloping of the aft cavity wall is successful. It is shown that the flow tends towards a steady state and the results are compared to the hypothesis of Heller and Bliss. This hypothesis is substantiated by the present simulations and in doing so the work demonstrates the ability of CFD to be used as a tool in conjunction with experimental methods to enhance the understanding of cavity flows. An area of cavity flows for which information is sparse is for the transitional cavity flows. A review of the literature shows that the 4 types of cavity flow exist at supersonic speeds and these are identified by the CFD. The results of the computational study are used to examine when the impingement and exit shocks, characteristic of closed cavity flow, collapse to form a single shock wave. This point is defined as L/Dcrit and occurs when the vertices of the separation and recompression wakes merge. It represents the boundary between transitional-closed flow and closed flow and the CFD predictions are compared to Prandtl-Meyer theory when investigating the position of L/Dcrit.
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Khorrami, Ahmad Farid. "Hypersonic aerodynamics on flat plates and thin aerofoils." Thesis, University of Oxford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.292584.

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Coverston, Joseph S. "Numerical Simulation of Flushing Deposits in Pipelines." FIU Digital Commons, 2019. https://digitalcommons.fiu.edu/etd/3951.

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The purpose of this research is to reduce the amount of waste generated in Department of Energy nuclear cleanup efforts currently underway. Due to the highly radioactive nature of the waste, any fluid that contacts the waste must then be treated and processed as waste. To minimize the fluids contaminated during flushing, this research aims to provide a basis for the flushing of High Level Waste (HLW) pipelines. Edgar Plastic Kaolin (EPK) with solid particles of a nominal diameter of 1 micron was used as a simulacrum for HLW. An Eulerian-Eulerian simulation built in StarCCM+ software, with a k-ω turbulence model, and a drag coefficient to connect the solid EPK phase with the liquid phase, was used to simulate the flushing of pipelines. Velocities from 3 ft/s to 10 ft/s were investigated to find the highest volumetric efficiency, and it was determined that 10 ft/s was the optimal flushing velocity.
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Sharpe, Jacob Andrew. "3D CFD Investigation of Low Pressure Turbine Aerodynamics." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1495872867696744.

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Menzies, Ryan D. D. "Investigation of S-shaped intake aerodynamics using computational fluid dynamics." Thesis, University of Glasgow, 2002. http://theses.gla.ac.uk/1440/.

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Flows in the s-shaped intake (Royal Aircraft Establishment intake model 2129-M2129) have been simulated and analysed using Computational Fluid Dynamics (CFD). Various flows have been simulated from steady through-flow for validation and verification, steady flows at a variety of angles of pitch and yaw, and the unsteady flow of surge wave propagation following the application of surge signatures at the engine face. Reynolds Averaged Navier-Stokes (RANS) simulations have been considered using the SA, k- ω and SST turbulence models where possible. The freestream Mach number was fixed at 0.21 and the Reynolds number based on the non-dimensional engine face diameter was 777,000 for all cases. The Glasgow flow solver PMB was used and second order accuracy was achieved in both space and time. Grid and time step convergence studies verified the numerical method, the grids being of the structured multi-block type. A comprehensive validation study was undertaken on the steady through-flow problem. Previously examined low and high mass flow cases were studied. It was found that the low mass flow results compared well with previous computational solutions. Problems however were encountered in the quantitative prediction of the secondary flow when compared with experiment however the SST model did quantitatively predict this. The high mass flow case proved more challenging. Solutions predicted two different flow regimes depending on the turbulence model used. It was found that the SST model provided a good matched with the primary set of experimental data. Confidence in this result was gained as it also performed well in the low mass flow case and also as it has shown previous improvements in the prediction of separation in flows with strong adverse pressure gradients.
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Books on the topic "Fluid- and Aerodynamics"

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Chattot, Jean-Jacques. Computational Aerodynamics and Fluid Dynamics. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-662-05064-4.

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Tucker, Paul G. Advanced computational fluid and aerodynamics. Cambridge: University of Cambridge, 2016.

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Engineers, Society of Automotive, and SAE International Congress & Exposition (1992 : Detroit, Mich.), eds. Vehicle aerodynamics: Wake flows, computational fluid dynamics, and aerodynamic testing. Warrendale, PA: Society of Automotive Engineers, 1992.

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1936-, Thornton Earl A., Wieting A. R, and Langley Research Center, eds. Fluid-thermal-structural study of aerodynamically heated leading edges. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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1936-, Thornton Earl A., Wieting A. R, and Langley Research Center, eds. Fluid-thermal-structural study of aerodynamically heated leading edges. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Chattot, Jean-Jacques. Computational Aerodynamics and Fluid Dynamics: An Introduction. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002.

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United States. National Aeronautics and Space Administration., ed. Interactive computer graphics applications for compressible aerodynamics. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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Center, Ames Research, ed. A Perspective of computational fluid dynamics. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1986.

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A, Arndt Roger E., American Society of Civil Engineers. Aerospace Division., American Society of Civil Engineers. Engineering Mechanics Division., and American Society of Civil Engineers. Hydraulics Division., eds. Advancements in aerodynamics, fluid mechanics, and hydraulics: Proceedings of the specialty conference. New York, N.Y: The Society, 1986.

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K, Bose T. Computational fluid dynamics. New York: Wiley, 1988.

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Book chapters on the topic "Fluid- and Aerodynamics"

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Pozrikidis, C. "Aerodynamics." In Fluid Dynamics, 606–50. Boston, MA: Springer US, 2001. http://dx.doi.org/10.1007/978-1-4757-3323-5_12.

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Pozrikidis, C. "Aerodynamics." In Fluid Dynamics, 803–51. Boston, MA: Springer US, 2016. http://dx.doi.org/10.1007/978-1-4899-7991-9_12.

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Pozrikidis, Constantine. "Aerodynamics." In Fluid Dynamics, 680–727. Boston, MA: Springer US, 2009. http://dx.doi.org/10.1007/978-0-387-95871-2_12.

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Liu, Peiqing. "Fundamentals of Viscous Fluid Dynamics." In Aerodynamics, 235–305. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4586-1_5.

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Liu, Peiqing. "Foundation of Fluid Kinematics and Dynamics." In Aerodynamics, 85–187. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4586-1_3.

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Liu, Peiqing. "Plane Potential Flow of Ideal Incompressible Fluid." In Aerodynamics, 189–233. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4586-1_4.

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Hucho, Wolf-Heinrich, Klaus Hannemann, Jan Martinez Schramm, and Charles Williamson. "Aerodynamics." In Springer Handbook of Experimental Fluid Mechanics, 1043–155. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-30299-5_16.

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Liu, Peiqing. "Aerodynamics." In A General Theory of Fluid Mechanics, 79–174. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-6660-2_2.

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Visconti, Guido, and Paolo Ruggieri. "Aerodynamics and All That." In Fluid Dynamics, 85–116. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-49562-6_4.

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Zierep, Jürgen, and Karl Bühler. "Hydro- and Aerodynamics." In Principles of Fluid Mechanics, 51–191. Wiesbaden: Springer Fachmedien Wiesbaden, 2022. http://dx.doi.org/10.1007/978-3-658-34812-0_4.

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Conference papers on the topic "Fluid- and Aerodynamics"

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Li, Pei, Richard Seebass, and Helmut Sobieczky. "Oblique flying wing aerodynamics." In Theroretical Fluid Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-2120.

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Morishita, E. "BIPLANE AERODYNAMICS REVISITED." In Topical Problems of Fluid Mechanics 2016. Institute of Thermomechanics, AS CR, v.v.i., 2016. http://dx.doi.org/10.14311/tpfm.2016.019.

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Venkataraman, P., Chris Nilsen, and Kenneth Corey. "Airgun pellet performance using computational fluid dynamics." In 12th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1940.

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Johnson, D., F. Menter, and C. Rumsey. "The status of turbulence modeling for external aerodynamics." In Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2226.

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Iosilevskii, Gil, and Yuval Levy. "Aerodynamics of the Cyclogiro." In 33rd AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3473.

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LEE, K. "Application of computational fluid dynamics in transonic aerodynamicdesign." In 11th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3481.

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Mattsson, Ken, Magnus Svärd, Mark Carpenter, and Jan Nordström. "Accuracy Requirements for Transient Aerodynamics." In 16th AIAA Computational Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3689.

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Mange, R., and F. Roos. "The aerodynamics of a chined forebody." In 29th AIAA, Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2903.

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Turkel, E., and E. Turkel. "Preconditioning-squared methods for multidimensional aerodynamics." In 13th Computational Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2025.

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JAMESON, ANTONY. "Successes and challenges in computational aerodynamics." In 8th Computational Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1184.

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Reports on the topic "Fluid- and Aerodynamics"

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MacCormack, Robert W. Magneto-Fluid Dynamics Calculations for Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, November 2007. http://dx.doi.org/10.21236/ada474960.

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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). Warrendale, PA: SAE International, October 2005. http://dx.doi.org/10.4271/2005-32-0033.

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Leidermark, Daniel, and Magnus Andersson, eds. Reports in Applied Mechanics 2022. Linköping University Electronic Press, February 2024. http://dx.doi.org/10.3384/9789180754156.

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Abstract:
This is the first volume of the concurring series of Reports in Applied Mechanics, which is based on the outcome of the advanced project course TMPM07 in Applied Mechanics at Link¨oping University during the autumn of 2022. The course lay-up is based on several industrial related projects within the field of Solid Mechanics, concerning fatigue, topology optimisation, structural dimensioning, contacts etc, and Fluid Mechanics, concerning fluid dynamics, flow, aerodynamics, heat transfer etc. The students tackle industry relevant projects in close collaboration with industry from near and neighbouring regions and work in project groups to solve the given tasks within the time limit of the course. Close collaboration with the industry is necessary to define planning, update and feedback for further evaluation at the industry. Three projects were performed during the course of 2022, two within Solid Mechanics and one in Fluid Mechanics. The projects were all performed in tight collaboration with industry partners, and had a close application to real industrial problems. A good opportunity for the students to show-off all their gained knowledge and apply in the best possible way to make innovative solutions in the respective projects. Something they all managed to do with success!
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Sahu, Jubaraj, Harris L. Edge, Karen R. Heavey, and Earl N. Ferry. Computational Fluid Dynamics Modeling of Multi-body Missile Aerodynamic Interference. Fort Belvoir, VA: Defense Technical Information Center, August 1998. http://dx.doi.org/10.21236/ada354107.

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Vaughn, Jr, Auman Milton E., and Lamar M. An Assessment of Productive Computational Fluid Dynamics for Aerodynamic Design. Fort Belvoir, VA: Defense Technical Information Center, January 2008. http://dx.doi.org/10.21236/ada476334.

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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. Fort Belvoir, VA: Defense Technical Information Center, February 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. Fort Belvoir, VA: Defense Technical Information Center, February 1998. http://dx.doi.org/10.21236/ada353756.

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Zheng, Wanzheng, and Jason Merret. Aerodynamic Survey of Novel eVTOL Configuration Using SU2. Illinois Center for Transportation, August 2022. http://dx.doi.org/10.36501/0197-9191/22-014.

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This report summarizes computational fluid dynamics (CFD) results of electric vertical takeoff and landing (eVTOL) geometries using the SU2 Reynolds-averaged Navier-Stokes (RANS) solver. Geometries were generated based on the Smart Transportation Infrastructure Initiative (STII) Rappor 15th iteration with various rotor-installment solutions. It was found that although open rotors installed on an underwing pylon were superior to shrouded rotors installed in a canoe, the canoe configuration would provide more potential for improvement, and using a canoe door to cover the first rotor opening would reduce the drag experienced by the canoe case below that upon the rod case. Rotor doors were found to be most efficient in reducing drag of the canoe case: Average drag reduction with covering the first rotor and all rotors was 66 and 165 counts, respectively. Changing rotor distributions along the chordwise direction had minimal impact on drag reduction, and placing rotors along the spanwise direction was not advised due to the increase of the projected frontal area. Increasing canoe chord length did not have significant impact on drag reduction; and if rotor doors were implemented, increasing canoe size had negative impact on drag. Rounding rotor edges did not change the aerodynamic performance of the canoe case but promotes vertical air intake when running lifting fans. Drag received by the canoe parabolically correlated to rotor diameter, with 126 counts of drag if the rotor diameter was 0 and 377 counts if the rotor diameter was 2.95 ft. Fuselage and tail added an average 179 counts of drag, and thus the aforementioned differences were still significant in the scale of aerodynamic properties of the full configuration.
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Kokes, Joseph, Mark Costello, and Jubaraj Sahu. Generating an Aerodynamic Model for Projectile Flight Simulation Using Unsteady, Time Accurate Computational Fluid Dynamic Results. Fort Belvoir, VA: Defense Technical Information Center, September 2006. http://dx.doi.org/10.21236/ada457421.

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