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Relevant bibliographies by topics / Aerofoils

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Academic literature on the topic 'Aerofoils'

Author: Grafiati

Published: 4 June 2021

Last updated: 29 July 2024

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Journal articles on the topic "Aerofoils"

1

Radwan M. Aljuhashy. "Numerical Study For Slotted And Vibrated Asymmetric Aerofoils." Wasit Journal of Engineering Sciences 11, no. 3 (December 2, 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 slotted aerofoils then subjected to an oscillatory motion due to the wind flow with 15Hz frequency.

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2

Zhang, Hailang, Yu Hu, and Gengqi Wang. "The effect of aerofoil camber on cycloidal propellers." Aircraft Engineering and Aerospace Technology 90, no. 8 (November 5, 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 ones. Findings The cycloidal propeller with large cambered aerofoil gives the lowest hovering efficiency, but with symmetrical aerofoil or small inverse cambered aerofoil shows the highest. Also, blades with large cambered aerofoil display high performance at the upper part of its trajectory, while with symmetrical aerofoil or the inverse cambered aerofoil have their best at the lower part. In addition, intensified downwash can be observed in the rotor cage for all cases. When a blade runs through the top-left part of its circle path, all cases display the feature of deep dynamic stall. When the blade travels through the nadir of its path, the actual angle of attack is close to zero due to the strong downwash. Furthermore, there exits intensified blade-vortex interaction induced by the preceding blade for large cambered aerofoils at the lower-right part of its trajectory. Practical implications This paper develops a new cycloidal propeller which is more efficient than the one already present. Originality/value This paper discovers that the aerofoil camber is a vital design parameter in the performance of cycloidal propeller, and the authors expect that the rotor with deformable aerofoil on camber would achieve much higher efficiency.

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3

Baddoo, P. J., and L. J. Ayton. "Potential flow through a cascade of aerofoils: direct and inverse problems." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 474, no. 2217 (September 2018): 20180065. http://dx.doi.org/10.1098/rspa.2018.0065.

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The potential flow through an infinite cascade of aerofoils is considered as both a direct and inverse problem. In each case, a perturbation expansion about a background uniform flow is assumed where the size of the perturbation is comparable to the aspect ratio of the aerofoils. This perturbation must decay far upstream and also satisfy particular edge conditions, including the Kutta condition at each trailing edge. In the direct problem, the flow field through a cascade of aerofoils of known geometry is calculated. This is solved analytically by recasting the situation as a Riemann–Hilbert problem with only imaginary values prescribed on the chords. As the distance between aerofoils is taken to infinity, the solution is seen to converge to a known analytic expression for a single aerofoil. Analytic expressions for the surface velocity, lift and deflection angle are presented as functions of aerofoil geometry, angle of attack and stagger angle; these show good agreement with numerical results. In the inverse problem, the aerofoil geometry is calculated from a prescribed tangential surface velocity along the chords and upstream angle of attack. This is found via the solution of a singular integral equation prescribed on the chords of the aerofoils.

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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 aerodynamic performance of the original and modified aerofoils. These results are compared with experimental data obtained from tests on the original aerofoil geometry. The computed aerodynamic advantages of the modified aerofoil are analysed in different operating conditions. The leading edge singularity of NACA0012 is removed and it is shown that the surface curvature discontinuity affects the aerodynamic performance near the stalling angle of attack. The discontinuous slope-of-curvature distribution of E387 influences the size of the laminar separation bubble at lower Reynolds numbers, and it affects the inherent profile of the aerofoil at higher Reynolds numbers. It is concluded that the surface curvature distribution of aerofoils has a significant effect on aerofoil aerodynamic performance, which can be improved by redesigning the surface curvature distribution of the original aerofoil geometry.

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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 (May 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 environment. To design aerofoils suitable for low Reynolds number MAV applications, we optimize a high RLD aerofoil by inducing transition to improve the effective aerofoil shape in the flow field. The study reveals that excessive curvature can suppress the formation of laminar separation bubbles at the leading edge, redirecting separation to the midsection. This results in reduced aerofoil drag and enables a high lift distribution at the leading edge.

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Crowdy, Darren. "Calculating the lift on a finite stack of cylindrical aerofoils." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 462, no. 2069 (January 24, 2006): 1387–407. http://dx.doi.org/10.1098/rspa.2005.1631.

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The classic exact solution due to Lagally (Lagally, M. 1929 Die reibungslose strömung im aussengebiet zweier kreise. Z. Angew. Math. Mech . 9 , 299–305.) for streaming flow past two cylindrical aerofoils (or obstacles) is generalized to the case of an arbitrary finite number of cylindrical aerofoils. Given the geometry of the aerofoils, the speed and direction of the oncoming uniform flow and the individual round-aerofoil circulations, the complex potential associated with the flow is found in analytical form in a parametric pre-image region that can be conformally mapped to the fluid region. A complete determination of the flow then follows from knowledge of the conformal mapping between the two regions. In the special case where the aerofoils are all circular, the conformal mapping from the parametric pre-image region to the fluid domain is a Möbius mapping. The solution for the complex potential in such a case can then be used, in combination with the Blasius theorem, to compute the distribution of hydrodynamic forces on the multi-aerofoil configuration.

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He, W., and X. Liu. "Improved aerofoil parameterisation based on class/shape function transformation." Aeronautical Journal 123, no. 1261 (March 2019): 310–39. http://dx.doi.org/10.1017/aer.2018.165.

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ABSTRACTA new aerofoil parameterisation method is put forward to represent an aerofoil by combining the leading edge modification class/shape function transformation (LEM CST) method and improved Hicks–Henne bump function’s method. The new class/shape function transformation (NEW CST) method has two additional basis functions comparing the original CST method. In order to confirm these two basis functions, the radial basis functions neural network (RBF) model is trained by some samples which are generated by the Latin hypercube design (LHD) method and Genetic Algorithm (GA) is proposed to achieve the basis functions of the NEW CST method. The NEW CST method has been evaluated in fitting precision of 1,545 aerofoils by comparison with the LEM CST method and the original CST method. And the improved ability of the NEW CST at the leading edge and trailing edge is verified by a series of complex aerofoil case studies within 1,545 aerofoils. The results indicate that the NEW CST method can represent the whole aerofoils and possesses the intuitive property as well as the original CST. Moreover, the number of control parameters (NCP) to parameterise aerofoils is the fewest among these three methods. Furthermore, when the NCP of the NEW CST and LEM CST is the same, the NEW CST method has the higher accuracy and smaller root mean square errors (RMSE) especially at the leading edge and trailing edge.

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Laratro, Alex, Maziar Arjomandi, Benjamin Cazzolato, and Richard Kelso. "Self-noise of NACA 0012 and NACA 0021 aerofoils at the onset of stall." International Journal of Aeroacoustics 16, no. 3 (April 2017): 181–95. http://dx.doi.org/10.1177/1475472x17709929.

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The aerodynamic noise of a NACA 0012 and NACA 0021 aerofoil is measured and compared in order to determine whether there are differences in their noise signatures with a focus on the onset of stall. Measurements of the self-noise of each aerofoil are measured in an open-jet Anechoic Wind Tunnel at Reynolds numbers of 64,000 and 96,000, at geometric angles of attack from −5° through 40° at a resolution of 1°. Further measurements are taken at Re = 96,000 at geometric angles of attack from −5 through 16° at a resolution of 0.5°. Results show that while the noise generated far into the stall regime is quite similar for both aerofoils the change in noise level at the onset of stall is significantly different between the two aerofoils with the NACA 0021 exhibiting a much sharper increase in noise levels below a chord-based Strouhal number of Stc = 1.1. This behaviour is consistent with the changes in lift of these aerofoils as well as the rate of collapse of the suction peak of a NACA 0012 aerofoil under these flow conditions.

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Kozic, M. S., and D. Sredojevic. "Development of unstructured dynamic grids for solving unsteady two-dimensional Euler equations." Aeronautical Journal 102, no. 1014 (April 1998): 195–200. http://dx.doi.org/10.1017/s0001924000096305.

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AbstractA method for the solution of the time dependent Euler equations on unstructured grids is presented for unsteady flows about oscillating aerofoils. The flow solver involves a finite volume spatial discretisation and a Runge-Kutta time-stepping scheme. A dynamic mesh algorithm is used for problems where the aerofoil moves and/or deforms. Steady and unsteady results are obtained for single and multi-element aerofoils.

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Campanile, L. F., and G. Thwapiah. "A non-linear theory of torsional divergence." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, no. 11 (September 11, 2009): 2707–11. http://dx.doi.org/10.1243/09544062jmes1843.

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In recent years, research on aerofoil morphing is increasingly focusing on innovative ideas such as the use of compliant systems and the exploitation of aeroelastic servo-effects. If brought to their limit, these concepts would allow operating aerofoils in aeroelastically marginally stable or even unstable conditions. In this view, a non-linear approach to aeroelastic torsional divergence becomes relevant. This article presents an extension of the well-known linear theory of divergence, which takes into account non-linear effects of structural as well as aerodynamic nature. The non-linear theory is applied to the case of a thin aerofoil and the pre-critical as well as post-critical response is computed for selected values of the flow parameters. Instability curves are also included, which show the aerofoil's torsional deformation as a function of the dynamic pressure, for selected values of an imposed disturbance.

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Dissertations / Theses on the topic "Aerofoils"

1

Reid, Michael R. "Thin/cambered/reflexed airfoil development for micro-air vehicles at Reynolds numbers of 60,000 to 150,000 /." Electronic version of thesis, 2006. https://ritdml.rit.edu/dspace/handle/1850/2607.

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2

Huang, Liang. "Optimization of blowing and suction control on NACA0012 airfoil using genetic algoirthm with diversity control." Lexington, Ky. : [University of Kentucky Libraries], 2004. http://lib.uky.edu/ETD/ukymeen2004d00153/LiangDis.pdf.

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Thesis (M.S.)--University of Kentucky, 2004.
Title from document title page (viewed Oct. 12, 2004). Document formatted into pages; contains xii, 113 p. : ill. Includes abstract and vita. Includes bibliographical references (p. 102-112).

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Janjua, Zaid Ayaz. "Ice accretion on aerofoils." Thesis, University of Nottingham, 2017. http://eprints.nottingham.ac.uk/45409/.

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Ice accretion on aerofoils is a problematic phenomenon affecting power lines, ships and aircraft wings. This work thus undertakes an experimental and computational investigation into the formation and adhesion of ice on aerofoils. An experimental setup to test the adhesion strength of ice was designed and tested for repeatability and the effect of temperature on it. It was found that the ambient temperature has a profound effect on the adhesion strength, possibly due to dependence on the heat transfer mechanism through an amorphous liquid-like layer between ice and substrate. The tests were expanded to determine the effect of contact angle parameters on the icephobicity of 14 nanocoatings. It was found that the surface should possess high receding contact angle and low CAH to reduce adhesion thereby reducing the ice-substrate contact points. Hydrophobicity and icephobicity may not necessarily be dual characteristics of a surface unless the aforementioned criteria is satisfied. Anti-icing tests on the same coatings showed that the freezing time of a droplet on the surface reduces with an increase in static contact angle. To understand the role of mixed ice, a one dimensional model is introduced to measure the accretion of mixed, rime and glaze ice on an aerofoil. This process occurs in four distinct stages and the effect of atmospheric parameters on the transition time between different growth types and height is determined. This mode was developed further to include a convective term to determine the profile of ice when rime grows above glaze/mixed with water flowing inside. This is a first step towards understanding the links between porous structures, ice structures and runback water that can generate interesting icy structures. This work forms part of the ICECOAT project funded by the EU Framework 7 CleanSky programme under grant award JTI-CS-2012-02-SFWA-01-051.

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4

Arbos, Torrent Sara. "Aeromechanical performance of compliant aerofoils." Thesis, Imperial College London, 2013. http://hdl.handle.net/10044/1/28105.

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The aeromechanics of compliant aerofoils are studied. Several experimental techniques including hot-wire anemometry, particle image velocimetry, high speed photogrammetry and strain gauge force measurements are used. Tests are performed at a chord based Reynolds number of Re= 4x10^4 and angles of attack between 0° and 25°. They explore the impact of the geometry of the leading- and trailing-edge supports as well as the rigid- ity of the aerofoil on the aeromechanics and aerodynamics of membrane aerofoils. Tests on latex membrane wings subjected by four different types of supports are performed. Firstly, the study focuses on the structural performance by evaluating detailed measure- ments of membrane deflections and lift and drag forces. It will be shown that the use of lower bending stiffness supports results in noticeable deformations, both static and dynamic, especially at mid-to-high incidences. Moreover, the conjunction of hot-wire results with photogrammetry imagery of the membrane deformation indicates that the membrane vibration is coupled with the vortex shedding. This, when coupled with a low-stiffness rectangular cross-section leading- and trailing-edge, results in large amplitude vibrations affecting the membrane, the support and the wake. Hence, a more detailed study of the vortex shedding and the wake attributes is presented. The findings indicate that for low angles of attack the wake characteristics are highly affected by the leading- and trailing- edge geometry; as incidence increases the wake characteristics become less dependant on the support's geometry, eventually reaching a point in which they are fully independent of it and closely resembling a fully stalled rigid aerofoil. Finally, the effects of the aero- foil rigidity are analysed. Tests of varying thickness but constant Young's modulus on unidirectional carbon fibre composite plates are performed. Results show that the Weber number is a crucial parameter when defining the properties and performance of the wing. Furthermore, the study will show that lift and drag forces are higher for membrane wings than for composite plates and that the dynamic motions of the composite plates increase as the plate thickness is decreased resulting in earlier wing stall and worse post-stall be- haviour than membrane wings. The results of this study should provide valuable insight for future use of membrane wings in micro air vehicles.

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Nash, Emma Clare. "Boundary layer instability noise on aerofoils." Thesis, University of Bristol, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.337698.

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6

Tse, Man-Chun. "Overall effects of separation on thin aerofoils." Thesis, McGill University, 1991. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=74592.

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The separation bubble at the leading edge of a thin sharp-edged aerofoil in steady, incompressible and two-dimensional flow was studied. A simple method, using irrotational flow and source singularities, has been developed for predicting bubble reattachment length, drag and lift.
For a flat-plate aerofoil predictions compare favourably with new experiments. The non-dimensional reattachment length $x sb R over rm c$ is proportional to the square of the incidence $( alpha)$ and the slope $x sb R over rm c alpha sp2$ depends on the growth of the outer part of the separated shear layer. The value of the term $x sb R over rm c alpha sp2$ was determined experimentally as $ pi over 0.08$. At incidences above 2$ sp circ$, the bubble drag becomes increasingly dominant when compared with the skin friction drag. Although the details of the bubble geometry are not simulated, the lift and stall are predicted fairly well.
The theory is extended to a circular-arc aerofoil. This part of the study is much less satisfactory. New experimental measurements do not appear to be sufficiently accurate to provide the empiricism to support the extended theory which must now account for regions of separated flow near the trailing edge.

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Suddhoo, A. "Inviscid compressible flow past multi-element aerofoils." Thesis, University of Manchester, 1985. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.356714.

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Palmer, Nathaniel Thomas. "Surge-induced deflections of axial compressor aerofoils." Thesis, Cranfield University, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.442401.

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Scarbrough, William T. "NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section /." Online version of thesis, 1992. http://hdl.handle.net/1850/11033.

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Chantharasenawong, Chawin. "Nonlinear aeroelastic behaviour of aerofoils under dynamic stall." Thesis, Imperial College London, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.440548.

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Books on the topic "Aerofoils"

1

Mueller, T. J. The structure of separated flow regions occuring near the leading edge of airfoils including transition. [Washington, DC: National Aeronautics and Space Administration, 1987.

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Srinivasan, G. Computations of two-dimensional airfoil-vortex interactions. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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M, Russell Louis, Torres Felix J, and United States. National Aeronautics and Space Administration., eds. Use of a liquid-crystal, heater-element composite for quantitative, high-resolution heat transfer coefficients on a turbine airfoil, including turbulence and surface roughness effects. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1987.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Inviscid analysis of two supercritical laminar-flow-control airfoils at design and off-design conditions. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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M, Russell Louis, Torres Felix J, and United States. National Aeronautics and Space Administration., eds. Use of a liquid-crystal, heater-element composite for quantitative, high-resolution heat transfer coefficients on a turbine airfoil, including turbulence and surface roughness effects. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1987.

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M, Russell Louis, Torres Felix J, and United States. National Aeronautics and Space Administration., eds. Use of a liquid-crystal, heater-element composite for quantitative, high-resolution heat transfer coefficients on a turbine airfoil, including turbulence and surface roughness effects. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1987.

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Wigley, D. A. Technology for pressure-instrumented thin airfoil models. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Srinivasan, G. Computations of two-dimensional airfoil-vortex interactions. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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1936-, Tung C., and Ames Research Center, eds. Suppression of dynamic stall with a leading-edge slat on a VR-7 airfoil. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1993.

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United States. National Aeronautics and Space Administration., ed. Final report for modeling of heavy-gas effects on airfoil flows. [Washington, DC: National Aeronautics and Space Administration, 1992.

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Book chapters on the topic "Aerofoils"

1

Wood, David. "Aerofoils: Lift, Drag, and Circulation." In Small Wind Turbines, 57–75. London: Springer London, 2011. http://dx.doi.org/10.1007/978-1-84996-175-2_4.

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Baddoo, Peter Jonathan. "Potential Flow Through Cascades of Thin, Impermeable Aerofoils." In Springer Theses, 21–55. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-55781-2_2.

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Baddoo, Peter Jonathan. "Scattering by Cascades of Aerofoils with Realistic Geometry." In Springer Theses, 57–138. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-55781-2_3.

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Baddoo, Peter Jonathan. "Potential Flow Through Cascades of Thin, Porous Aerofoils." In Springer Theses, 139–63. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-55781-2_4.

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Render, P. M., J. L. Stollery, and B. R. Williams. "Aerofoils at Low Reynolds Numbers—Prediction and Experiment." In Numerical and Physical Aspects of Aerodynamic Flows III, 155–67. New York, NY: Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4926-9_9.

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Baddoo, Peter Jonathan. "Scattering by Cascades of Aerofoils with Complex Boundary Conditions." In Springer Theses, 165–212. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-55781-2_5.

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Baddoo, Peter Jonathan. "Potential Flow Through Cascades with Multiple Aerofoils per Period." In Springer Theses, 213–39. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-55781-2_6.

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Roohani, H., and B. W. Skews. "Transient aerodynamic forces experienced by aerofoils in accelerated motion." In Shock Waves, 1065–70. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_44.

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Stolcis, Luca, and Leslie J. Johnston. "Computation of the Viscous Flow Around Multi-Element Aerofoils Using Unstructured Grids." In Proceedings of the Ninth GAMM-Conference on Numerical Methods in Fluid Mechanics, 311–20. Wiesbaden: Vieweg+Teubner Verlag, 1992. http://dx.doi.org/10.1007/978-3-663-13974-4_30.

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Roohani, H., and B. W. Skews. "Effect of acceleration on shock-wave dynamics of aerofoils during transonic flight." In Shock Waves, 1401–6. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_98.

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Conference papers on the topic "Aerofoils"

1

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 Reynolds number aerofoils is of particular importance in their successful application. Test results show the LP turbine performance to be in line with expectation. Measured aerofoil pressure distributions are presented and compared with the design intent. Changes in the turbine characteristics relative to the original design are interpreted by making reference to the detailed differences in the two aerofoil design styles.

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Eckel, Jannik, and Volker Gümmer. "Numerical Investigation of the Aerodynamic Performance of Hybrid Aerofoils in a 1.5-Stage Low-Speed Compressor." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-58657.

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Abstract This paper describes the numerical investigation of hybrid aerofoils in a 1.5-stage low-speed compressor, which in its baseline configuration features a conventional rotor and a tandem stator. Both of these are eventually replaced by hybrid aerofoils, using the initial tandem blade profile geometry around mid-span. In this course of design investigations a pure tandem rotor was also generated and analysed as the initial geometry of the hybrid rotor. The aerodynamic design and performance of the tandem rotor and the hybrid aerofoils will be discussed in this paper. The numerical analysis is aimed at understanding the secondary flow phenomena and limiting factors of the working range of the reference stage. Based on this knowledge, the advantages of the hybrid aerofoil design will be discussed. On one hand, the origin and development of three-dimensional flow structures near the endwall regions of the rear vane of the tandem stator are investigated in detail, as they appear to play a major role at de-throttled operating conditions. On the other hand, the tip vortex leakage of the single rotor and the pure tandem rotor are considered, showing the tip vortex taking a major role in loss generation and stall inception at throttled operating conditions, and interacting with the tandem stator secondary flow phenomena at the casing. Both these performance-limiting factors can be addressed by implementing hybrid aerofoils. The paper presents and discusses the improvement of secondary flow loses and aerodynamic performance based on steady-state RANS simulations.

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Petrenko, Victor, and Zoe Courville. "Active de-icing coating for aerofoils." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-632.

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Dhiliban, A., P. Meena, P. S. Narasimhan, and M. Vivek. "Aerodynamic Performance of Rear Roughness Aerofoils." In Eighth Asia-Pacific Conference on Wind Engineering. Singapore: Research Publishing Services, 2013. http://dx.doi.org/10.3850/978-981-07-8012-8_252.

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Senoo, Shigeki. "Development of Design Method for Supersonic Turbine Aerofoils Near the Tip of Long Blades in Steam Turbines: Part 1—Overall Configuration." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68218.

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The purpose of this paper is development of the design method for supersonic turbine aerofoils. In particular, a design method is established for four fundamental parameters which determine the overall configuration of the aerofoils: inlet angle, outlet angle, pitch-to-chord ratio, and stagger angle. The developed design method is constructed as follows. Three parameters of a velocity triangle, the inlet flow angle, inflow Mach number and pressure ratio, are selected as predetermined design parameters. The inlet angle is coincident with the inlet flow angle. The outlet angle is formulated as a function of the three design parameters using aerodynamic theory. An allowable design space between the pitch-to-chord ratio and the stagger angle is clarified by formulating three geometrical constraints to accelerate supersonic flow smoothly. The three geometrical constraints are the inlet and outlet flow passage areas derived from the design parameters and the no-inflection-point condition on the aerofoil surface. Good performance of supersonic turbine aerofoils designed by the developed method is confirmed using computational fluid dynamics. There is no strong shock wave. When there is no solution in the theoretical allowable design space because of the large pitch-to-chord ratio required for low centrifugal stress, the following two methods enable the feasible design space to be enlarged without a large increase in the energy loss. One is to ease the restriction of the outlet flow passage area. The other is to increase the outlet flow angle of the pressure surface by about 10 deg in the axial direction from the theoretical angle. Their effectiveness is also validated by computational fluid dynamics.

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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-dimensional optimisation of a highly loaded compressor stator is presented. For optimisation a novel methodology based on the Multipoint Approximation Method (MAM) is used. MAM makes use of an automatic design of experiments, response surface modelling and a trust region to represent the design space. The CFD solutions are obtained with the high-fidelity 3D Navier-Stokes solver HYDRA. In order to increase the stage performance the 3D shape of the tandem vane is modified changing both the front and rear aerofoils. Moreover the relative location of the two aerofoils is controlled modifying the axial and tangential relative positions. It is shown that the novel optimisation methodology is able to cope with a large number of design parameters and produce designs which performs better than its single vane counterpart in terms of efficiency and numerical stall margin. One of the key challenges in producing an automatic optimisation process has been the automatic generation of high-fidelity computational meshes. The multi block-structured, high-fidelity meshing tool PADRAM is enhanced to cope with the tandem blade topologies. The wakes of each aerofoil is properly resolved and the interaction and the mixing of the front aerofoil wake and the second tandem vane are adequately resolved.

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Schlieter, T., and A. Długosz. "STRUCTURAL OPTIMIZATION OF AEROFOILS FOR MANY CRITERIA." In Engineering Mechanics 2020. Institute of Thermomechanics of the Czech Academy of Sciences, Prague, 2020. http://dx.doi.org/10.21495/5896-3-448.

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Woodley, B., N. Peake, B. Woodley, and N. Peake. "Vortex shedding from a cascade of aerofoils." In 28th Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1814.

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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 the passage vortex plays an important role in the downstream flow field and loss behaviour. It was concluded that the aerofoil loading distribution has a significant influence on the strength of this vortex. In contrast, the leading-edge geometry appears to have only a minor influence on the secondary flow field, at least for the design incidence.

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