Relevant bibliographies by topics / Aerofoil

Academic literature on the topic 'Aerofoil'

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Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Aerofoil"

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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 (July 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 as the objective function. The aerodynamic performance of the aerofoil was calculated by combining the XFOIL program and Viterna–Corrigan post-stall model, while the aerofoil's performance was validated with computational fluid dynamic simulations. The results illustrated that, compared to an unoptimized NACA0015 aerofoil, the optimized aerofoil's lift to drag ratio was improved over a wide range of attack angles and the stall performance was gentler. The maximum lift coefficient, the maximum lift to drag ratio and the maximum tangential force coefficient were increased by 7.5%, 9% and 8.87%, respectively. Finally, this paper predicted the rotor efficiency with both the unoptimized and optimized NACA0015 aerofoils for different TSRs and different solidities using the multiple streamtube model. The results showed that the rotor with the optimized aerofoil has a higher efficiency.
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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 (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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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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., Sundram, and Rahul Kumar. "Investigation of Airfoil Design and Analysis." International Journal for Research in Applied Science and Engineering Technology 10, no. 10 (October 31, 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 into two categories - they are Asymmetrical and Symmetrical aerofoils. Based on their drag and lift coefficient’s variation with angle of attack, stall angle of attack and magnitude of the coefficients they are divided. Here the NACA aerofoil is modified by adding dimples on the upper half of the wing and compared with the simple one. The comparison is made on different speed and pressure on the wing and the coefficient of lift and drag.
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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 (August 15, 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 carried out using ANSYS FLUENT. Lift and Drag forces along with the angle of attack are the important parameters in a wind turbine system. These parameters decide the efficiency of the wind turbine. The lift force and drag force acting on aerofoil were determined with various angles of attacks ranging from 0° to 12° and wind speeds. The coefficient of lift and drag values are calculated for 1×105 Reynolds number. The pressure distributions as well as coefficient of lift to coefficient of drag ratio of this aerofoil were visualized. The CFD simulation results show close agreement with those of the experiments, thus suggesting a reliable alternative to experimental method in determining drag and lift.
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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 (May 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 (August 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 caused by the repair sheets was also investigated. Finally, the numerical solution was qualitatively and quantitatively validated using the available experimental results.
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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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Haselbach, Frank, Heinz-Peter Schiffer, Manfred Horsman, Stefan Dressen, Neil Harvey, and Simon Read. "The Application of Ultra High Lift Blading in the BR715 LP Turbine." Journal of Turbomachinery 124, no. 1 (February 1, 2001): 45–51. http://dx.doi.org/10.1115/1.1415737.

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The original LP turbine of the BR715 engine featured “High Lift” blading, which achieved a 20-percent 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 percent 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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Wibowo, Heri. "Pengaruh Sudut Serang Aerofoil Terhadap Distribusi Tekanan dan Gaya Angkat." JURNAL DINAMIKA VOKASIONAL TEKNIK MESIN 2, no. 2 (October 1, 2017): 148. http://dx.doi.org/10.21831/dinamika.v2i2.15999.

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The aerofoils are used to get the lifting force on the design of plane’s wings. The lifting force is caused by difference air velocity on upper and lower aerofoil which the magnitude depend on attack angle of aerofoil and air velocity exist surrounding. This experiment aims to show the force vector (pressure distribute) on the aerofoil. The aerofoil is attached by air with konstant velocity. The research procedure is done by change the attack angle of aerofoil on five formation. The surface of aerofoil is connected with pressure gage which disperse at 11 point of measurement. The result shows that magnitude of force vector is depended on attack angle of aerofoil. Increasing angle of aerofoil until boundary angle will be followed by increasing air velocity on the point of measurement and finally increase force vector. Upper boundary angle will be followed by decreasing air velocity and finally decrease force vector.Aerofoil digunakan untuk mendapatkan gaya angkat pada desain sayap pesawat. Gaya angkat disebabkan oleh perbedaan kecepatan udara pada aerofoil atas dan bawah yang besarnya tergantung pada sudut serang aerofoil dan kecepatan udara yang ada disekitarnya. Eksperimen ini bertujuan untuk menampilkan vektor gaya (distribusi tekanan) pada aerofoil. Aerofoil dilekatkan pada udara dengan kecepatan konstan. Prosedur penelitian dilakukan dengan cara mengubah sudut serang aerofoil pada lima formasi. Permukaan aerofoil dihubungkan dengan alat ukur tekanan yang tersebar pada 11 titik pengukuran. Hasil menunjukkan bahwa besarnya vektor gaya bergantung pada sudut serang aerofoil. Sudut aerofoil yang meningkat hingga sudut batas akan diikuti dengan peningkatan kecepatan udara pada titik pengukuran dan akhirnya meningkatkan vektor gaya. Sudut batas atas akan diikuti oleh penurunan kecepatan udara pada titik pengukuran dan akhirnya menurunkan vektor gaya.
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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 exit of the tunnel. Airflow speeds from 10m/s to 40m/s and a range of angles of incidence were investigated. A number of modifications were made to reduce the noise and improve the operation of the wind tunnel. Different methods of measuring the aeroacoustic noise produced by an aerofoil were also investigated. The theory of aeroacoustic noise generation is described and the effect of a scattering surface on the efficiency of these aeroacoustic noise sources was investigated. A number of different mechanisms by which an aerofoil produces aeroacoustic noise were identified. These mechanisms were divided into three main categories: (1) blunt trailing edge aerofoil noise (2) sharp trailing edge aerofoil noise and (3) stalled aerofoil noise. The effect of air temperature on the production of aeroacoustic noise was also investigated. It was found that in most instances air temperature would have little effect on aeroacoustic noise generation. An extensive study of the aeroacoustic noise produced by a number of different aerofoils was undertaken. Modelling of the airflow over the aerofoils was used to determine the mechanism by which aeroacoustic noise is produced. Several different aeroacoustic noise generation mechanisms were identified. Theoretical models were also used to model the aeroacoustic noise produced by the aerofoils. Several treatments to reduce the level of aeroacoustic noise produced by an aerofoil were investigated. The treatments reduced the aeroacoustic noise produced by an aerofoil with varying degrees of success. A method for measuring the aeroacoustic noise produced by car roof racks mounted on the roof of a vehicle using a relatively small wind tunnel was established. The noise level produced by a roof rack installed 011 the roof of a vehicle measured using this technique compared favourably with measurements made on a full vehicle in a large wind tunnel. The method shows promise as a low cost method of accurately measuring the aeroacoustic noise produced by roof racks installed on a vehicle roof.
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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 of the flow is developed; and it is shown that, under certain conditions, a similar flow pattern can be set up in a stationary model. Measurements of the flow in a machine are reported and a comparison is made with results from such a stationary model. It is concluded that, although discrepancies may arise from wall friction, Coriolis and centrifugal effects, or the variation in density, the stationary model is nevertheless capable of providing useful information about the loss-producing mechanisms in the flow. The results of more detailed measurements on stationary models of two different designs are presented, on the basis of which suggestions are made for an improved design of machine. The analysis is extended to include Coriolis and centrifugal effects, and the influence which the position of the blades relative to the machine axis has on the performance of the machine is examined. The presence of a uniform component of vorticity normal to the blade-to-blade plane is a characteristic feature of regenerative turbomachines. Some effects of this are discussed, and a computer program written to calculate the two-dimensional, inviscid, incompressible flow through a cascade with such a uniform spanwise vorticity is described.
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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 with previous work, they show that variations in aerofoil parameters, such as aerofoil thickness, leading edge nose radius and camber, produce only a small changes in broadband interaction noise at approach conditions. Subsequent chapters deal with the development of innovative leading edge serration profiles aimed at reducing interaction noise. Chapter 4 is a detailed study into the limitations of single-wavelength serrations in reducing interaction noise. The optimum profile is identified. Chapters 5, 6 and 7 all deal with the development of innovative profiles that can provide up to 10dB of additional noise reductions compared to single-wavelength serrations. For each of the profiles investigated a simple model is developed to aid the understanding of their interaction mechanism.
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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 are simulated using strip theory, which computes the flows in multiple two-dimensional planes located at intervals along the wing span. The flows are assumed locally. two-dimensional and the three-dimensional effects between each section are incorporated via the consideration of vortex lattice effects. The simulations are modelled using piecewise linear finite element approximation method on an unstructured triangular finite element mesh. A dynamic moving mesh is used to compute flexible aerofoils and wings. The mesh is remeshed at each fluid time step using the spring segment analogy method. A novel treatment of the near.-wall viscous grids ensures that the good orthogonal properties are maintained to facilitate the turbulence computations. A wide range of simulations is carried out for an oscillatory heaving NACA0012 aerofoil. Parametric studies of basic parameters like the amplitude of oscillation, its reduced frequency, and the flow freestream Reynolds numbers effects on aero foil performance are conducted. The influences of the flexural profile on the flexible aerofoil propulsive characteristics are also investigated. The rectangular wing, oflow aspect ratio 4 and NACA0012 aerofoil cross-sections, is also simulated in oscillatory heaving motion. The chordwise flexural effects of the heaving flexible wing on its propulsive characteristics are studied too.
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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 blades. Deviation from a small optimal range of tip speed ratios results in poor performance. The Darrieus also has poor starting torque. The research conducted in this project focused on overcoming the shortcomings of other turbines and developing an effective cross flow turbine capable of good performance. A number of different concepts were experimented with, however all were based on a symmetrical aerofoil presented to the actual relative airflow at an angle that would produce the highest lift force at all times. The lift force was then utilized to generate movement and to do work on an electrical generator. All concepts contemplated were researched to ascertain their appropriateness for the intended application. During development of the final experimental platform and after lodging of a provisional patent (RSA 2007/00927) it was ascertained that the design shared some similarities with an American patent 5503525 dated 28/4/1994. This patent employed complex electronic sensing and control equipment for control of blade angle. This was thought to be overly complex and costly, particularly for small scale wind energy generation applications and a simpler mechanical solution was sought in the design of the final experimental platform used in this project. The design of the mechanical control system was refined in an attempt to make it simpler, more durable and employ the least number of moving parts. Literature studies and patent searches conducted, suggested that the mechanical control system as developed for the final experimental platform was unique. The enormous variation in the power available from the wind at the different wind speeds likely to be encountered by the device necessitated some means of control. In high wind conditions control of the amount of wind power into the device was deemed to be the preferable means of control. A number of different concepts to achieve this were devised and tested. The final concept employed limited the tail angle deflection and hence the lift produced by the aerofoils. This resulted in a seamless “throttle” control allowing the device to be used in any wind strength by adjusting the control to a position that resulted in the device receiving a suitable amount of power from the wind. The outcome of performance tests conducted indicated that the device has the potential to be developed into a viable wind turbine for both small and large scale applications. The ability to control the power input from the wind to the machine from zero to a maximum is considered to be one of the most beneficial outcomes of this project and together with the quiet operation and low speed, are considered the main advantages of the device over existing wind turbine designs. The possibilities of using the device to compress air for energy storage are exciting avenues that warrant further research.
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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. Koch's (1985) global mode selection criteria is applied to the wake and is found to give good agreement with the experimentally measured vortex formation frequency. This implies the existence of a critical profile in the wake which, in conjunction with the aerofoil trailing edge, traps energy at the vortex formation frequency. At higher chord Reynolds numbers, (17000 to 300000), the vortex formation characteristics of the aerofoil are further examined both with and without the excitation of an acoustic resonance. Detailed phase averaged measurements of the aerofoil wake are made allowing examination of its structure during resonance. A novel scheme for the accurate measurement of vortex phase is introduced, based on comparison of vortical structure of the vortex formation region using two-dimensional cross-correlation. The results obtained support a modified version of the acoustic resonance excitation mechanism proposed by of Arbey and Bataille (1983). Vortex street structures considerably different to the classic Kármán vortex street are observed. For antisymmetric streets, the vortex spacing ratio h/l is shown to be widely different from the theoretical value of 0.281 obtained by von Kármán and Rubach.
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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. Manchester: UMIST, 1995.

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

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

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

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

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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. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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

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

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The enigma of the aerofoil: Rival theories in aerodynamics, 1909-1930. Chicago: The University of Chicago Press, 2011.

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

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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, 55–100. Berlin, Heidelberg: 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, 237–63. Dordrecht: 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, 801–11. Singapore: 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, 1–22. Cham: 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, 319–24. Dordrecht: 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, 211–20. London: 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, 951–61. Singapore: 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, 521–27. Cham: 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, 27–39. Cham: 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, 253–59. Berlin, Heidelberg: 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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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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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, the aerofoil without P-Pins was also tested to provide baseline results. The measurements have been made at engine representative Mach and Reynolds numbers. Wide band liquid crystal and direct heat flux gauge technique were employed in the heat transfer tests. A four-hole pyramid probe was used to obtain the aerodynamic data. The aerodynamic and thermodynamic characteristics of the coolant flow have been modelled to represent engine conditions by using a heavy “foreign gas” (30.2% SF6 and 69.8% Ar by weight). The paper concludes that P-Pins as usually placed on the blade do not have detrimental effects to the heat transfer performance of film-cooled aerofoil. P-Pins, located in thick boundary layer regions of the aerofoil, such as the later portion of the suction surface, do not cause any reduction of aerofoil aerodynamic efficiency. For contrast, the P-Pins located in the thin boundary layer regions on the pressure side of the aerofoil cause noticeably more losses.
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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 capacity and bearing thrust load variation. This paper deals with a generic approach to visualise the variation of capacity and bearing thrust load with aerofoil skew for a stage of interest along with the Constraints that could be potentially imposed on the stage. This methodology provides a useful mapping between parameters which are directly under the aerodynamicist’s control (i.e. aerofoil skew) to module- and system-level behaviours (i.e. capacity, bearing thrust load). It thereby allows informed choices to be made throughout the design process which deliver the turbine aerodynamic performance targets whilst respecting wider system-level constraints. Suitable optimisation within this design space will yield a design that is fundamentally robust to small deviations in skew angle. Additionally, qualitative variation of the gas path static pressure and reaction based on aerofoil skews are explained pictorially to facilitate the understanding.
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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 viscosity on temperature. Flow is taken as first order upwind and flux type is AUSM (Advection Upstream Splitting Method) to get an exact resolution of contact and shock discontinuities. The distribution of temperature, pressure, velocity and streamline of fluid flow is numerically simulated by FLUENT 16 software and layout of eddies generation behind aerofoil is generated in Tecplot 360 software. The coefficient of lift (Cl) and the coefficient of drag (Cd) are calculated to study the impact on aerofoil blade in horizontal and vertical direction. The result indicates that the method presented in this paper can analyze the fluid behavior on the complicated geometry of aerofoil blade that the flow between two adjacent aerofoil blades obtains a highly reliable simulation result. The value of lift force is negative i.e it holds the deflector towards the ground, so optimum balance between drag force and lifts force is obtained by simulating at a different angle of attack and pitch. Through CFD numerical simulation at a different angle of attack and pitch, the best result is obtained and conductive suggestions can be given for the adaptation of the JBD blade.
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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 is performed for different angles of attack and the Co-efficients of Drag (Cd) and Lift (C1) are validated with the experimental results of Gilarranz et al. [1]. The flow is simulated by solving Unsteady RANS coupled with k-ε realizable turbulence model with enhanced wall treatment. Synthetic jet is placed in NACA0015 airfoil at 12% of the chord length with width as 0.53% of chord and is studied for a Reynolds number Re = 8.96 × 105 and for angle of attack from 12 to 20 degrees [2]. The jet is almost tangential to the wall at an angle, αjet = 10° and chord length is considered as 0.375m for the study. Further, parametric analyses are conducted on NACA 0015 aerofoil to investigate effect of parameters (frequency, jet angle, jet velocity). It is observed that aerofoil’s performance is improved significantly for jet angle (30°–40°), jet frequency (100 Hz) and non dimensional jet velocity (1.8–2.0). A maximum increase of approximately 26% in Lift was observed at AOA 20°.
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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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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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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 higher than that of the corresponding isolation aerofoil, under the designed work conditions, at the same angle and the same place. On the same aerofoil, the change of pressure of aerofoil of the blade cascade is less than the pressure of the isolation aerofoil on high pressure side, but it was opposite on low pressure side.
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Adami, P., F. Martelli, K. S. Chana, and F. Montomoli. "Numerical Predictions of Film Cooled NGV Blades." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38861.

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Film-cooling is commonly used in modern gas turbines to increase inlet temperatures without compromising the mechanical strength of the hot components. The main objective of the study reported here is the critical evaluation of the capability of CFD, to predict film-cooling on three-dimensional engine realistic turbine aerofoil geometries. To achieve this aim two different film-cooling systems for NGV aerofoils are predicted and compared against experiments. The application concerns the following turbine vanes: • the AGTB-B1 blade investigated by the “Institut fur Strahlantriebe of the Universitat der Bundeswehr Munchen (Germany)”; • the MT1 HP NGV investigated by QinetiQ (ex DERA, UK). In the first test case the application mainly focuses on the interaction between the main flow and the coolant jets on the leading edge of the cooled aerofoil. In the second case, vane heat transfer rate is predicted with the film-cooling system made of six rows of cylindrical holes in single and staggered configuration.
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Hield, Paul. "Semi-Inverse Design Applied to an Eight Stage Transonic Axial Flow Compressor." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50430.

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Semi-Inverse Design is a class of Computational Fluid Dynamics (CFD) procedures for calculating aerofoil geometry from prescriptions of pressure loading and thickness distribution; when describing an aerofoil in three dimensions a stacking axis is also needed. All sixteen blade rows of an eight stage transonic axial flow compressor have been simultaneously designed in a single inverse 3D CFD calculation. The tip Mach number of the first rotor was just over sonic with a peak value in excess of 1.25. Apart from the substitution of geometric by aerodynamic aerofoil boundary conditions, the CFD model is the same as that used for direct analysis and includes rotor and stator clearance gaps as well as stator shroud leakage flows. This has profound implications for 3D CFD in the context of the total design process at a system level. The technique allows 3D CFD to behave like a design point through flow in the sense that we can now ask the question of 3D CFD - “what is the performance of a turbo-machine that has this design intent?” as opposed to “does this set of aerofoils meet the design intent and if they do what is its performance? And if they do not how should they be changed?” Inverse design provides a means of conveying design intent up through the “fidelity levels” from 1-D and 2-D, through Low Fidelity 3D CFD to High Fidelity CFD. Thus the desired loading distribution may be determined cheaply using 2D blade to blade analysis, either by iterative direct analysis (the current approach) or using a semi-inverse technique in 2D. As an illustration of this, a 1-D tool will be presented which produces estimates of aerofoil shape and surface velocities in real time to enable the designer to manipulate the loading distributions which are then used in Inverse 3D CFD to realize the final geometry.
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