Relevant bibliographies by topics / Aerofoil

Contents

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

Academic literature on the topic 'Aerofoil'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 July 2025

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Journal articles on the topic "Aerofoil"

1

Liang, Changping, and Huaxing Li. "Aerofoil optimization for improving the power performance of a vertical axis wind turbine using multiple streamtube model and genetic algorithm." Royal Society Open Science 5, no. 7 (2018): 180540. http://dx.doi.org/10.1098/rsos.180540.

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This paper reports on the optimization of the NACA0015 aerofoil for improving the power performance of a vertical axis wind turbine (VAWT). The target range of the chord Re is 3 × 10 5 –10 6 , the tip speed ratio (TSR) is 2–6 and the solidity is 0.2–0.6. This aerofoil is widely applied in small-scale VAWTs. In the optimization process, in which the class and shape function transformation parametrization method was used to perturb the aerofoil geometry, the thickness and camber of the aerofoil were selected as the constraints and the value of the maximum tangential force coefficient was chosen
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Zhang, Hailang, Yu Hu, and Gengqi Wang. "The effect of aerofoil camber on cycloidal propellers." Aircraft Engineering and Aerospace Technology 90, no. 8 (2018): 1156–67. http://dx.doi.org/10.1108/aeat-08-2016-0128.

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Purpose This paper aims to investigate the impact of aerofoil camber on the performance of micro-air-vehicle-scale cycloidal propellers. Design/methodology/approach First, experiments were conducted to validate the numerical methodology. After that, three turbulent models were compared to select the most accurate one. Then, 2D numerical simulation was carried out on 11 aerofoils with different cambers, including five cambered aerofoils, one symmetrical aerofoil and five inverse cambered aerofoils. The inverse cambered aerofoils are symmetrical about the chord line to the corresponding cambered
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Radwan M. Aljuhashy. "Numerical Study For Slotted And Vibrated Asymmetric Aerofoils." Wasit Journal of Engineering Sciences 11, no. 3 (2023): 34–44. http://dx.doi.org/10.31185/ejuow.vol11.iss3.496.

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The aerodynamics of slotted aerofoils under various Reynolds numbers were numerically studied. Moreover, vibration of aerofoils due to the wind flow was also investigated. Different Reynolds numbers (0.25, 0.4, 0.7 and 1) ×106 were utilized using an Ansys noncommercial version. A slotted asymmetric aerofoil, which was NACA4412, was chosen to implement the concept of the current investigation. The base aerofoil was compared to an experimental study to check the number of cells above and around the aerofoil. The slotted aerofoil appeared to have more momentum on the suction side. Moreover, the s
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Shen, Xiang, Theodosios Korakianitis, and Eldad Avital. "Numerical Investigation of Surface Curvature Effects on Aerofoil Aerodynamic Performance." Applied Mechanics and Materials 798 (October 2015): 589–95. http://dx.doi.org/10.4028/www.scientific.net/amm.798.589.

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The prescribed surface curvature distribution blade design (CIRCLE) method optimises aerofoils and blades by controlling curvature continuity and slope of curvature distribution along their surfaces. The symmetrical NACA0012 exhibits a surface curvature discontinuity at the leading edge point, and the non-symmetrical E387 exhibits slope-of-curvature discontinuities in the surface. The CIRCLE method is applied to both aerofoils to remove both surface curvature and slope-of-curvature discontinuities. Computational fluid dynamics analyses are used to investigate the curvature effects on aerodynam
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., Sundram, and Rahul Kumar. "Investigation of Airfoil Design and Analysis." International Journal for Research in Applied Science and Engineering Technology 10, no. 10 (2022): 863–80. http://dx.doi.org/10.22214/ijraset.2022.47087.

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Abstract: In this project “Aerofoil Design and Analysis” an attempt has made to make a complete study on lift and drag coefficient of various aerofoil sections using CFD. The primary goal of this project is to learn and analyse the aerodynamic performance of wings. The objective of this study is to improve aerofoil design using the software CATIA, And Fluent Analysis using the software ANSYS. Aerofoil is a principal part of any airplane construction. How much lift force and drag force is sufficient to balance the weight of the plane is decided by the aerofoil. Aerofoils are basically divided i
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Liu, Haoji, Weicheng Di, Zixing Wei, Daochun Li, Jingwu Xiang, and Zhan Tu. "Aerodynamic optimization design of low reynolds number aerofoils based on induced laminar separation." Journal of Physics: Conference Series 2764, no. 1 (2024): 012019. http://dx.doi.org/10.1088/1742-6596/2764/1/012019.

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Abstract At low Reynolds numbers, the design of aerofoils with a high lift-to-drag ratio (RLD) is crucial for enhancing the aerodynamic performance of Micro Air Vehicles (MAVs). However, the transition from laminar to turbulent flow plays a dominant role in the aerodynamic performance of aerofoils at Low-Reynolds-Numbers (LRN). The laminar separation bubbles formed in laminar flow alter the effective aerofoil shape, reducing aerodynamic efficiency. Additionally, predicting the shape and location of the laminar separation bubbles becomes challenging due to its sensitivity to the flight environm
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., Albi, M. Dev Anand, and G. M. Joselin Herbert. "Aerodynamic Analysis on Wind Turbine Aerofoil." International Journal of Engineering & Technology 7, no. 3.27 (2018): 456. http://dx.doi.org/10.14419/ijet.v7i3.27.17997.

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The aerofoils of wind turbine blades have crucial influence on aerodynamic efficiency of wind turbine. There are numerous amounts of research being performed on aerofoils of wind turbines. Initially, I have done a brief literature survey on wind turbine aerofoil. This project involves the selection of a suitable aerofoil section for the proposed wind turbine blade. A comprehensive study of the aerofoil behaviour is implemented using 2D modelling. NACA 4412 aerofoil profile is considered for analysis of wind turbine blade. Geometry of this aerofoil is created using GAMBIT and CFD analysis is ca
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Zhou, Zhiyuan. "The Development and Prospect of Micro Air Vehicles." Applied and Computational Engineering 130, no. 1 (2025): 108–18. https://doi.org/10.54254/2755-2721/2025.20283.

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This paper systematically reviews the evolution of Micro Air Vehicle (MAV) aerofoil design, covering the geometric optimization and development from fixed-wing, rotary-wing, and flapping-wing to biomimetic-wing designs. In low Reynolds number environments, there are four main types of fixed-wing aerofoils, considered the classic designs for MAVs and have significantly contributed to the future development of MAV aerofoils. Rotary-wing and flapping-wing MAVs represent the initial application of bionics in aerofoil design. At the same time, the lift mechanisms discovered in insects and birds hav
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Zachariou, E., P. Wilmott, and A. D. Fitt. "A cavitating aerofoil with a Prandtl-Batchelor eddy." Aeronautical Journal 98, no. 975 (1994): 171–76. http://dx.doi.org/10.1017/s000192400004985x.

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Abstract A simple model is presented for an aerofoil with a recirculating Prandtl-Batchelor region behind a spoiler. Using thin aerofoil theory the model is posed as a pair of coupled nonlinear singular integrodifferential equations for the shape of the separating streamline and the distribution of vorticity along the aerofoil. These equations are solved numerically and results are presented. In particular, some conclusions are drawn regarding the lift on such aerofoils.
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Saeedi, M., F. Ajalli, and M. Mani. "A comprehensive numerical study of battle damage and repairs upon the aerodynamic characteristics of an aerofoil." Aeronautical Journal 114, no. 1158 (2010): 469–84. http://dx.doi.org/10.1017/s0001924000003961.

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Abstract A NACA 641-412 aerofoil with circle and star damage and also three repair configurations has been numerically investigated. Two different methods of mesh generation were employed: multi structured mesh for the star damaged aerofoil and unstructured mesh for the other aerofoils. The results show that the damage will cause a reduction in lift coefficient of the aerofoil and also a different stall angle relative to that of the undamaged aerofoil. Each kind of repair improves the aerodynamic characteristics of the aerofoil considerably. The flow Field inside the damage hole and the cavity
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Dissertations / Theses on the topic "Aerofoil"

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Kingan, Michael Joseph. "Aeroacoustic noise produced by an aerofoil." Thesis, University of Canterbury. Mechanical Engineering, 2005. http://hdl.handle.net/10092/6596.

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This thesis describes an investigation into the aeroacoustic noise produced by an aerofoil using experimental, computational and theoretical methods. Several different types of aeroacoustic noise generation mechanisms and the parameters which affect these mechanisms were identified and investigated. The aerofoils used' in this investigation all had chord lengths of 100mm and had a maximum thickness between 18mm and 30mm. Experimental testing was undertaken in the low noise wind tunnel in the Department of Mechanical Engineering at the University of Canterbury with the aerofoils mounted at the
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Andrew, David Neil. "Flow in regenerative compressors with aerofoil blading." Thesis, University of Cambridge, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.235767.

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Regenerative compressors are low specific speed, tangential flow turbomachines in which the working fluid follows an approximately toroidal-helical path around the machine. Although regenerative turbomachines have been in use for over fifty years, the use of aerofoil blades (as opposed to the more usual straight vanes) is a relatively new innovation designed to improve the internal flow. However, little work has been done on the details of this flow. This dissertation concentrates on the flow in the main region of the compressor, away from the inlet and exit ports. A simple, analytical model o
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Khoo, Hilary. "Separated flow past wind turbine aerofoil sections." Thesis, Imperial College London, 1991. http://hdl.handle.net/10044/1/46866.

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Paruchuri, Chaitanya. "Aerofoil geometry effects on turbulence interaction noise." Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/415884/.

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Fan broadband is one of the dominant noise sources on an aircraft engine, particularly at approach. The dominant noise generation mechanism is due to turbulent- aerofoil interaction noise (TAI). This thesis investigates the effect of changes in 2D aerofoil geometry on TAI noise. The main focus of this thesis is to attempt to reduce it through the development of innovative leading edge geometries. The first two chapters of the thesis deals with an experimental and numerical investigation into the effect of aerofoil geometry on interaction noise on single aerofoils and on cascades. Consistent wit
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Crompton, Matthew John. "The thin aerofoil leading edge separation bubble." Thesis, University of Bristol, 2001. http://hdl.handle.net/1983/25312c88-4d89-4149-bee9-d56cf80d9735.

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Chew, Siou Chye. "Numerical simulations of oscillatory flapping aerofoil propulsion." Thesis, Imperial College London, 2011. http://hdl.handle.net/10044/1/8137.

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The primary objective of the current research is to develop a Computational Fluid Dynamics (CFD) model to investigate rigid and flexible aerofoil propulsive characteristics when the aerofoil IS subjected to oscillatory flapping motions. The study is also extended to rectangular wings. Flows past the flapping aero foils at moderate Reynolds numbers are simulated using the twodimensional incompressible Navier-Stokes equations. The Baldwin-Lomax algebraic turbulence model is incorporated to determine eddy viscosity for higher Reynolds numbers turbulent flow simulations. Flows past flapping wings
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Hustad, C. W. "The drag of a circulation controlled aerofoil." Thesis, University of Bath, 1986. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.370668.

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Phillips, Russell Leslie. "Development of a reciprocating aerofoil wind energy harvester." Thesis, Nelson Mandela Metropolitan University, 2008. http://hdl.handle.net/10948/899.

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Cross flow wind turbines are not unique. The performance of Savonius and Darrieus turbines is well documented. Both share the advantage of being able to accept fluid flow from any direction. The Savonius is drag based and hence has poor power output while the Darrieus is lift based. Due to the fact that the Darrieus has fixed blades the fluid flow through the rotor does not result in optimal lift being generated at all points in the rotation circle. A drawback of the Darrieus system is that it has to operate at a high tip-to wind-speed ratio to obtain reasonable performance with the fixed blad
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Gorman, J. "Vortex formation in the flow around a lifting aerofoil." Thesis, Swansea University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.637079.

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This thesis presents an investigation of vortex formation in the flow around a lifting aerofoil both with and without acoustic forcing. The chord Reynolds number range covered is from 3000 to 300000. At low chord Reynolds number, (3000 to 20000), and low incidence, (0 to 8°), vortex formation in the flow around an aerofoil has been studied in a water tunnel. Stability theory and in particular the concepts of absolute and convective instability are applied to the aerofoil wake. It is found that for non zero incidence a region of absolutely unstable flow is associated with the separation bubble.
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Baker, David. "Design of a morphing aerofoil using compliant structure optimisation." Thesis, University of Bristol, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.529826.

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Books on the topic "Aerofoil"

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Melocco, F. Computational method for high-lift aerofoil flows. UMIST, 1995.

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Lye, J. D. Recent developments in augmentor-wing aerofoil sections. De Havilland Aircraft Company of Canada, 1987.

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Papastavrou, P. Prediction of transition for high lift aerofoil systems. UMIST, 1996.

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Muhoho, A. P. Transonic Aerofoil computations using Grid Navier-Stokes Solver. UMIST, 1996.

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Fulker, J. L. Validation of cfd methods for transonic aerofoil and wing flows. HMSO, 1989.

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Moir, I. R. M. Measurements on a two-dimensional aerofoil with high-lift devices. Defence Research Agency, 1994.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. Aerofoil testing in a self-streamlining flexible walled wind tunnel. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Fulker, J. L. Study of simulated active control of shock waves on an aerofoil. Defence Research Agency, 1993.

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Ashill, P. R. A novel technique for controlling shock strength of laminar-flow aerofoil sections. Defence Research Agency, 1993.

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Ashill, P. R. Wind tunnel experiments on aerofoil models for the assessment of computational flow methods. HMSO, 1988.

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Book chapters on the topic "Aerofoil"

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Doerffer, Piotr, Charles Hirsch, Jean-Paul Dussauge, Holger Babinsky, and George N. Barakos. "Biconvex Aerofoil (Stefan Leicher)." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-03004-8_3.

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Srivastava, R. S. "Shock Interaction with Moving Aerofoil." In Interaction of Shock Waves. Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1086-0_7.

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Dosi, Prateet, Prem Kumar Bharti, Niharika Borah, Anjan Barman, Mriganka Baishnab, and Soumyabrata Bhattacharjee. "Multi-objective Optimization of Aerofoil." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-4320-7_71.

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Santos Pereira, Ricardo. "Aerofoil Aerodynamics of Wind Energy Devices." In Handbook of Wind Energy Aerodynamics. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-05455-7_14-1.

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Pier, Benoît, and Nigel Peake. "Global nonlinear dynamics of thin aerofoil wakes." In Seventh IUTAM Symposium on Laminar-Turbulent Transition. Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-3723-7_51.

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De Falco, I., A. Della Cioppa, A. Iazzetta, and E. Tarantino. "M ijn Mutation Operator for Aerofoil Design Optimisation." In Soft Computing in Engineering Design and Manufacturing. Springer London, 1998. http://dx.doi.org/10.1007/978-1-4471-0427-8_23.

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Dogra, Amber Singh, and Amit Kumar Singh. "Modeling and Simulation of an Aerofoil Using Ansys." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2188-9_86.

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Veerasamy, Dhamotharan, and Chris Atkin. "Transition Due to Aerofoil-Wake Boundary Layer Interaction." In IUTAM Laminar-Turbulent Transition. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-67902-6_45.

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Pons, Arion, and Fehmi Cirak. "Three-Dimensional Flight Simulation with Transient Moving-Aerofoil Models." In IUTAM Symposium on Recent Advances in Moving Boundary Problems in Mechanics. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-13720-5_3.

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Lee, D. S., J. Periaux, K. Srinivas, L. F. Gonzalez, N. Qin, and E. Onate. "Shock Control Bump Design Optimization on Natural Laminar Aerofoil." In Computational Fluid Dynamics 2010. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17884-9_31.

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Conference papers on the topic "Aerofoil"

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GUO, YP. "FLOW-AEROFOIL INTERACTION SOUND OF SUPERSONIC AEROFOILS." In Acoustics '88. Institute of Acoustics, 2024. http://dx.doi.org/10.25144/21840.

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Haselbach, Frank, Heinz-Peter Schiffer, Mannfred Horsman, Stefan Dressen, Neil Harvey, and Simon Read. "The Application of Ultra High Lift Blading in the BR715 LP Turbine." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0436.

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The original LP turbine of the BR715 engine featured “High Lift” blading, which achieved a 20% reduction in aerofoil numbers compared to blading with conventional levels of lift - reported in Cobley et al. (1997). This paper describes the design and test of a re-bladed LP turbine with new “Ultra High Lift” aerofoils, achieving a further reduction of approximately 11% in aerofoil count and significant reductions in turbine weight. The design is based on the successful cascade experiments of Howell et al. (2000) and Brunner et al. (2000). Unsteady wake - boundary layer interaction on these low R
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Guo, S. M., M. L. G. Oldfield, and A. J. Rawlinson. "Influence of Discrete Pin Shaped Surface Roughness (P-Pins) on Heat Transfer and Aerodynamics of Film Cooled Aerofoil." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30179.

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The influence of localized pin-shaped surface roughness (P-Pins) on heat transfer and aerodynamics of a fully film cooled engine aerofoil has been studied in a transonic annular cascade. The “P-Pins”, present on some casting film cooled turbine blades and vanes, are the residues left in the manufacturing process. This paper investigates the effect of the P-Pins on the aerodynamic performance and measures the heat transfer consequences both for the aerofoils and the P-Pins. The effect on performance was determined independently on the pressure and suction surface of the aerofoil. For comparison
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Srinivasan, Karthik, Soumyik K. Bhaumik, and Lakshmanan Valliappan. "Towards Visualisation of Capacity, Bearing Thrust Load and Reaction Variation With Aerofoil Skew in a Gas Turbine." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2441.

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Abstract The requirements in the design of aerofoils for gas turbines are not limited to only meeting the aerothermal performance. A typical scenario for a turbine is to understand the impact of aerofoil skew on capacity, reaction and bearing thrust load. A means to achieve the target capacity could be by skewing the aerofoil. This, however, changes the stage reaction which in turn impacts the bearing thrust load. In the case of a multi stage turbine, the work split between the stages impacts the ratio of pressure drops and hence the contribution of the individual aerofoil rows to the overall
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Jaiswal, Abhijeet, Ashwin S. Dhoble, and D. J. Tidke. "High Compressible Flow Through Jet Blast Deflector." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4699.

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Jet blast impact on aerofoil blade of the deflector is studied which redirects the high energy exhaust of jet engine during the ground testing. The geometric model of aerofoils is designed with structured mesh around the aerofoil in rectangular domain generated in ICEM 16 software. The jet blast impact on aerofoil blade of the deflector is numerically simulated with SST k-ω model based on CFD theory. The fluid flow is high-speed compressible flow and flowing fluid air is considered as an ideal gas and also Sutherland’s law viscosity is applied to account for the dependence of molecular viscosi
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Khatri, Shubham, Surya Pratap Singh, and Anant Kumar Singh. "Magnetorheological Finishing of 3D Printed Free-Form Aerofoiled Surface." In ASME 2024 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2024. https://doi.org/10.1115/imece2024-144723.

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Abstract Polylactic acid (PLA) is popular in 3D printing due to its affordability, biodegradability, and user-friendly properties. Industries such as automotive, aerospace, and medical are increasingly integrating PLA-printed parts. In the present study, a 3D-printed aerofoil is taken as a 3D workpiece. The surface finish of aerofoil plays a crucial role in aviation and fluid dynamics. In aviation, it enhances efficiency in generating lift and stability. In fluid dynamics, it minimizes drag and reduces turbulence. The use of magnetorheological finishing (MRF) enhances the surface quality of ae
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Neve, Mayuresh, V. R. Kalamkar, and Akshay Wagh. "Numerical Analysis of NACA Aerofoil Using Synthetic Jet." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4587.

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Usually at high angle of attack, aerofoil stalls due to flow separation on suction surface of aerofoil. To delay the flow separation, pulsating jet arrangement, known as Synthetic jet is used in aerofoil. It is produced by periodic suction and ejection of fluid from an orifice. This condition can be achieved by inducing movement to diaphragm or by giving a zero mass flux sinusoidal boundary condition to the jet. This allows the reattachment of boundary layer which improves the lift and drag performance and angle at also delays stalling angle. In present study, CFD analysis on NACA0015 aerofoil
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Benner, M. W., S. A. Sjolander, and S. H. Moustapha. "The Influence of Leading-Edge Geometry on Secondary Losses in a Turbine Cascade at the Design Incidence." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38107.

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The paper presents detailed experimental results of the secondary flows from two large-scale, low-speed linear turbine cascades. The aerofoils for the two cascades were designed for the same inlet and outlet conditions and differ mainly in their leading-edge geometries. Detailed flow field measurements were made upstream and downstream of the cascades using three- and seven-hole pressure probes and static pressure distributions were measured on the aerofoil surfaces. All measurements were made exclusively at the design incidence. The results from this experiment suggest that the strength of th
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Li, Long, Rongxia Hu, Dan Li, and Fei Yang. "Properties of Aerofoil and Blade Cascade in Hydraulic Machinery." In ASME 2009 Fluids Engineering Division Summer Meeting. ASMEDC, 2009. http://dx.doi.org/10.1115/fedsm2009-78098.

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The hydrodynamic properties of the blade aerofoil differ from that of the airfoil of the blade cascade in a pump of low head. The numerical simulation of the flow quality in the impeller was made on a commercial axial pump of low head. The blade cascade flow in impeller was discussed, and the characteristic of the airfoil profile of the impeller blade was studied using the FLUENT software. The characteristic of the isolation aerofoil was compared with that of the aerofoil of impeller blade cascade. The research results show that the pressure on the surface of the aerofoil of blade cascade is h
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Schlaps, R. C., S. Shahpar, and V. Gümmer. "Automatic Three-Dimensional Optimisation of a Modern Tandem Compressor Vane." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26762.

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In order to increase the performance of a modern gas turbine, compressors are required to provide higher pressure ratio and avoid incurring higher losses. The tandem aerofoil has the potential to achieve a higher blade loading in combination with lower losses compared to single vanes. The main reason for this is due to the fact that a new boundary layer is generated on the second blade surface and the turning can be achieved with smaller separation occurring. The lift split between the two vanes with respect to the overall turning is an important design choice. In this paper an automated three
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