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Relevant bibliographies by topics / Vortex-motion. Boundary layer. Aerodynamics

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Academic literature on the topic 'Vortex-motion. Boundary layer. Aerodynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 19 February 2022

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Journal articles on the topic "Vortex-motion. Boundary layer. Aerodynamics"

1

Volchkov, �. P., S. V. Semenov, and V. I. Terekhov. "Aerodynamics of end-wall boundary layer in a vortex chamber." Journal of Applied Mechanics and Technical Physics 27, no. 5 (1987): 740–48. http://dx.doi.org/10.1007/bf00916149.

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2

Štorch, Vít, and Jiří Nožička. "CONTRA-ROTATING PROPELLER AERODYNAMICS SOLVED BY A 3D PANEL METHOD WITH COUPLED BOUNDARY LAYER." Acta Polytechnica 57, no. 5 (2017): 355. http://dx.doi.org/10.14311/ap.2017.57.0355.

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The aerodynamics of contra-rotating propellers is a complex three-dimensional problem of an unsteady flow, which is often approached by assuming numerous simplifications. Presented computational model combines a 3D panel method with a force-free vortex wake and a two-dimensional two-equation boundary layer model in an attempt to capture all the main contributing elements of the flow physics. An emphasis is placed on the interaction of the viscous boundary layer region with the inviscid region and the development of a portable method of their coupling. The kinematics of a force-free vortex wake

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3

Ayudia, Siti Aisyah, Artoto Arkundato, and Lutfi Rohman. "Study of Vortex Generator Effect on Airfoil Aerodynamics Using the Computational Fluids Dynamics Method." Computational And Experimental Research In Materials And Renewable Energy 3, no. 2 (2020): 23. http://dx.doi.org/10.19184/cerimre.v3i2.23547.

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The lift force is one of the important factors in supporting the aircraft flying capabilities. The airplane has a section called the aircraft wing. In particular, the wing section of aircraft is called the airfoil. One of the efforts to increase the lift force is to make the flow of air fluid at the top of the airfoil more turbulent. Turbulent flow can attract momentum from the boundary layer, the result of this momentum transfer has energy that is more resistant to the adverse pressure gradient which can trigger the flow separation. Efforts that can be made to reduce separation flow and incre

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4

Ibaraki, Seiichi, Tetsuya Matsuo, Hiroshi Kuma, Kunio Sumida, and Toru Suita. "Aerodynamics of a Transonic Centrifugal Compressor Impeller." Journal of Turbomachinery 125, no. 2 (2003): 346–51. http://dx.doi.org/10.1115/1.1540117.

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High-pressure ratio centrifugal compressors are applied to turbochargers and turboshaft engines because of their small dimensions, high efficiency, and wide operating range. Such a high-pressure ratio centrifugal compressor has a transonic inlet condition accompanied with a shock wave in the inducer portion. It is generally said that extra losses are generated by interaction of the shock wave and the boundary layers on the blade surface. To improve the performance of high-pressure ratio centrifugal compressor, it is necessary to understand the flow phenomena. Although some research works on tr

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5

Ladopoulos, E. G. "Nonlinear unsteady flow problems by multidimensional singular integral representation analysis." International Journal of Mathematics and Mathematical Sciences 2003, no. 50 (2003): 3203–16. http://dx.doi.org/10.1155/s0161171203112318.

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A two-dimensional nonlinear aerodynamics representation analysis is proposed for the investigation of inviscid flowfields of unsteady airfoils. Such problems are reduced to the solution of a nonlinear multidimensional singular integral equation as the source and vortex strength distributions are dependent on the history of these distributions on the NACA airfoil surface. A turbulent boundary layer model is further investigated, based on the formulation of the unsteady behaviour of the momentum integral equation. An application is finally given to the determination of the velocity and pressure

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6

JEONG, MIN-SOO, SEUNG-JAE YOO, and IN LEE. "WIND TURBINE AERODYNAMICS PREDICTION USING FREE-WAKE METHOD IN AXIAL FLOW." International Journal of Modern Physics: Conference Series 19 (January 2012): 166–72. http://dx.doi.org/10.1142/s2010194512008707.

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Wind turbine aerodynamics remains a particularly challenging and crucial research for wind energy industry. The blade element momentum theory is the most widely used in predicting the performance of wind turbine, since the method is simple and fast numerical algorithm. The flow field generated by rotary wing is considerably important and complicated, however, the BEM method has some limitations to model the unsteady effects. To overcome these limitations, the aerodynamic analysis using a time-marching free-vortex wake method was performed in this paper. Moreover, the inboard region of the blad

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7

Furukawa, M., M. Inoue, K. Saiki, and K. Yamada. "The Role of Tip Leakage Vortex Breakdown in Compressor Rotor Aerodynamics." Journal of Turbomachinery 121, no. 3 (1999): 469–80. http://dx.doi.org/10.1115/1.2841339.

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The breakdown of tip leakage vortex has been investigated on a low-speed axial compressor rotor with moderate blade loading. Effects of the breakdown on the rotor aerodynamics are elucidated by Navier–Stokes flow simulations and visualization techniques for identifying the breakdown. The simulations show that the leakage vortex breakdown occurs inside the rotor at a lower flow rate than the peak pressure rise operating condition. The breakdown is characterized by the existence of the stagnation point followed by a bubblelike recirculation region. The onset of breakdown causes significant chang

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8

Wellenberg, Sören, Markus Marnett, Benedikt Roidl, Davis Kirkendall, Frederik Thönnißen, and Wolfgang Schröder. "Assessment of a numerical design tool for pitching airfoils." Wind Engineering 43, no. 6 (2019): 639–56. http://dx.doi.org/10.1177/0309524x18821883.

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The aim of this study was to assess the applicability of a numerical design tool for pitching airfoils; by evaluating their aerodynamic performance comparing experimental and numerical data at different levels of complexity. Experimental findings of non-harmonically pitching airfoil configurations in a water tunnel at medium Reynolds numbers are compared to solutions of a modified double-wake vortex-panel method with boundary-layer formulation and unsteady Reynolds-averaged Navier–Stokes simulations. For steady-state airfoil configurations at high angle of attack, large eddy simulation data ar

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9

Gennaretti, M., and C. Ponzi. "Finite-state aerodynamic modelling for gust load alleviation of wing–tail configurations." Aeronautical Journal 103, no. 1021 (1999): 147–58. http://dx.doi.org/10.1017/s0001924000064964.

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Abstract A finite-state aerodynamics methodology is proposed for the analysis of the forces generated by a gust. To illustrate and assess the methodology, gust-response and gust-alleviation applications are included. Finite-state aerodynamics denotes a technique to approximate aerodynamic loads so as to yield an aircraft model of the type ẋ = Ax + Bu (state-space formulation). In this paper, a finite-state formulation is proposed to include the presence of a gust. The aerodynamic loads to be approximated are evaluated here by using a frequency-domain boundary-element formulation; the flow is a

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10

Anwar Bég, O., H. S. Takhar, G. Nath, and A. J. Chamkha. "Mathematical Modelling of Hydromagnetic Convection from a Rotating Sphere with Impulsive Motion and Buoyancy Effects." Nonlinear Analysis: Modelling and Control 11, no. 3 (2006): 227–45. http://dx.doi.org/10.15388/na.2006.11.3.14744.

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The convective heat transfer on a rotating sphere in the presence of magnetic field, buoyancy forces and impulsive motion is examined theoretically and numerically in this paper. We apply a boundary layer model comprising the balance equations for x and y direction translational momentum and heat transfer, and solve these coupled non-linear partial differential equations using Blottner’s finite-difference method [1]. The numerical solutions are benchmarked with the earlier study by Lee [2] on laminar boundary layer flow over rotating bodies in forced flow and found to be in excellent agreement

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Dissertations / Theses on the topic "Vortex-motion. Boundary layer. Aerodynamics"

1

Mathioulakis, Dimitri. "Vorticity shedding over two-dimensional bodies." Diss., This resource online, 1985. http://scholar.lib.vt.edu/theses/available/etd-09162005-115000/.

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2

Leslie, Martin. "Experimental and computational investigation of sub-boundary layer vortex generators." Thesis, Queen's University Belfast, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.326371.

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3

Schreiber, Olivier. "Aerodynamic interactions between bodies in relative motion." Diss., Georgia Institute of Technology, 1990. http://hdl.handle.net/1853/11693.

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4

Watterson, John Kenneth. "A new, pressure-based, unstructured mesh, Navier-Stokes solver and application to 3D compressible vortex/boundary layer interactions." Thesis, University of Cambridge, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.337910.

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5

Oorebeek, Joseph Mark. "Comparison of distributed suction and vortex generator flow control for a transonic diffuser." Thesis, University of Cambridge, 2014. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.708400.

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6

Gunasekaran, Sidaard. "Relationship Between the Free Shear Layer, the Wingtip Vortex and Aerodynamic Efficiency." University of Dayton / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1470231642.

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7

Chuang, Fu-sheng. "The interacting boundary layer and acoustic field generated by vortex motion /." The Ohio State University, 1986. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487266691096485.

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8

Linn, Anthony B. "A computational study of turbulent structure formation." Link to electronic thesis, 2007. http://www.wpi.edu/Pubs/ETD/Available/etd-042607-093941/.

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9

Harsh, Martin D. "An experimental investigation of a turbulent junction vortex." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/54526.

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An experimental study of the incompressible, three-dimensional, turbulent flow separation around the base of a bluff obstacle on a flat surface is described. The bluff obstacle is a streamlined, right circular cylinder mounted with its axis normal to the flat surface. The flow environment is characterized by a body Reynolds number of 183,000, based on the diameter of the circular cylinder. The study includes surface flow visualizations, surface pressure measurements, and mean flow measurements. The mean flow measurements consist of total pressure, static pressure, and velocity distributions in

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10

Nappo, Carmen Joseph. "A theoretical investigation of gravity-wave-generated stress and vorticity in the planetary boundary layer." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/25697.

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Books on the topic "Vortex-motion. Boundary layer. Aerodynamics"

1

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Vortex flow aerodynamics. AGARD, 1991.

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2

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Vortex flow aerodynamics. AGARD, 1991.

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3

Keener, Earl R. Flow-separation patterns on symmetric forebodies. Ames Research Center, 1986.

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4

Montgomery, Matthew D. A three-dimensional linearized unsteady Euler analysis for turbomachinery blade rows. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

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5

Rockwell, Donald. Free vorticity field-boundary layer conversions: Effect of boundary configuration and scale : progress report for NASA Langley Research Center. National Aeronautics and Space Administration, 1985.

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6

Westphal, R. V. Interaction between a vortex and a turbulent boundary layer. National Aeronautics and Space Administration, Ames Research Center, 1987.

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7

Rigby, David L. Unsteady stagnation-point heat transfer during passage of a concentrated vortex. National Aeronautics and Space Administration, 1989.

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8

Rigby, David L. Unsteady stagnation-point heat transfer during passage of a concentrated vortex. National Aeronautics and Space Administration, 1989.

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9

Hall, Philip. The inviscid secondary instability of fully nonlinear longitudinal vortex structures in growing boundary layers. National Aeronautics and Space Administration, Langley Research Center, 1990.

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10

Hall, Philip. On the initial stages of vortex wave interactions in highly curved boundary layer flows. National Aeronautics and Space Administration, Langley Research Center, 1993.

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Book chapters on the topic "Vortex-motion. Boundary layer. Aerodynamics"

1

"Correlations Between Pressure Fluctuation and Vortex Motion." In High Order Large Eddy Simulation for Shock-Boundary Layer Interaction Control by a Micro-ramp Vortex Generator, edited by Chaoqun Liu, Qin Li, Yonghua Yan, Yong Yang, Guang Yang, and Xiangrui Dong. Bentham Science Publishers Ltd., 2017. http://dx.doi.org/10.2174/9781681085975117020010.

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Conference papers on the topic "Vortex-motion. Boundary layer. Aerodynamics"

1

STRAUS, J., and R. MAYLE. "Boundary-layer measurements during a parallel blade-vortex interaction." In 10th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-2623.

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2

Raghunathan, S., M. O'Rourke, J. Watterson, R. Cooper, and E. Benard. "Passive vortex control jets for shock boundary layer interactions." In 17th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3196.

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3

VERHAAGEN, N., J. MEEDER, and J. VERHELST. "Boundary layer effects on the flow of a leading edge vortex." In 11th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3463.

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4

INGER, G. "Computational simulation of vortex generator effects on transonic shock/boundary layer interaction." In 6th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2590.

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5

WARD, KENNETH, and JOSEPH KATZ. "Boundary layer separation and the vortex structures around an inclined body of revolution." In 5th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2276.

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6

Canepa, Edward, Davide Lengani, Francesca Satta, Ennio Spano, Marina Ubaldi, and Pietro Zunino. "Boundary Layer Separation Control on a Flat Plate With Adverse Pressure Gradients Using Vortex Generators." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90809.

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The continuous tendency in modern aeroengine gas turbines towards reduction of blade count and ducts length may lead to aerodynamic loading increase beyond the limit of boundary layer separation. For this reason boundary layer separation control methods, up to now mostly employed in external aerodynamics, begin to be experimented in internal flows applications. The present paper reports the results of a detailed experimental study on low profile vortex generators used to control boundary layer separation on a large-scale flat plate with prescribed adverse pressure gradients. Inlet turbulent bo

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7

Ibaraki, Seiichi, Tetsuya Matsuo, Hiroshi Kuma, Kunio Sumida, and Toru Suita. "Aerodynamics of a Transonic Centrifugal Compressor Impeller." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30374.

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High pressure ratio centrifugal compressors are applied to turbochargers and turboshaft engines because of their small dimensions, high efficiency and wide operating range. Such a high pressure ratio centrifugal compressor has a transonic inlet condition accompanied with a shock wave in the inducer portion. It is generally said that extra losses are generated by interaction of the shock wave and the boundary layers on the blade surface. To improve the performance of high pressure ratio centrifugal compressor it is necessary to understand the flow phenomena. Although some research works on tran

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8

Srivastava, Smriti, and Sudipto Sarkar. "Wake Interaction of a Square Cylinder With a Splitter Plate Boundary Layer at a Low Reynolds Number." In ASME/JSME/KSME 2015 Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/ajkfluids2015-01793.

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One of the most important researches in bluff body aerodynamics is to control the shear layer evolution leading to vortex formation. This kind of research is closely associated with reduction of aerodynamics forces and acoustic noise. Passive and active control of wake-flow from bluff bodies have received a great deal of attention in the last few decades [1–4]. Keeping this in mind, authors investigate the interaction of a square cylinder (side of the square = a) wake with a flat plate (length L = a, width w = 0.1a) boundary layer positioned at various downstream locations close to the cylinde

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9

Prothin, Sebastien, Henda Djeridi, and Jean-Yves Billard. "Effect of Longitudinal Vortex on Boundary Layer State and Separation on NACA Symmetric Foil." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-30992.

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Vortex generators have been widely used in aerodynamics to control the separation of boundary layers. In such application (Angele and Muhammad, 2005) vortex generators are embedded in the boundary layer and the vortex height, with regards to the wall, is of the boundary layer thickness. The objective of this configuration is obviously far from being the effects of a single longitudinal vortex (generated upstream by an elliptical plan form profile) on the turbulent boundary layer shape over a Naca0015 symmetric foil at different incidences at high Reynolds number 5 105. The vortex is situated o

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10

Furukawa, Masato, Masahiro Inoue, Kazuhisa Saiki, and Kazutoyo Yamada. "The Role of Tip Leakage Vortex Breakdown in Compressor Rotor Aerodynamics." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-239.

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The breakdown of tip leakage vortex has been investigated on a low-speed axial compressor rotor with moderate blade loading. Effects of the breakdown on the rotor aerodynamics are elucidated by Navier-Stokes flow simulations and visualization techniques for identifying the breakdown. The simulations show that the leakage vortex breakdown occurs inside the rotor at a lower flow rate than the peak pressure rise operating condition. The breakdown is characterized by the existence of the stagnation point followed by a bubble-like recirculation region. The onset of breakdown causes significant chan

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