Relevant bibliographies by topics / Thin Cambered Airfoil

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  2. Dissertations / Theses
  3. Books
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Academic literature on the topic 'Thin Cambered Airfoil'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Thin Cambered Airfoil"

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Ali, Nesar, Mostafizur Rahman Komol, and Mohammad Takiuddin Saki. "Study on Thin Airfoil Theory & Performance Test of Elliptical Wing as Compared to Model Mosquito Wing and NACA 64A012 Mod Airfoil." European Journal of Engineering Research and Science 3, no. 4 (2018): 48. http://dx.doi.org/10.24018/ejers.2018.3.4.665.

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Thin airfoil theory is a simple conception of airfoils that describes angle of attack to lift for incompressible, inviscid flows. It was first devised by famous German-American mathematician Max Munk and therewithal refined by British aerodynamicist Hermann Glauertand others in the 1920s. The thin airfoil theory idealizes that the flow around an airfoil as two-dimensional flow around a thin airfoil. It can be conceived as addressing an airfoil of zero thickness and infinite wingspan. Thin airfoil theory was particularly citable in its day because it provided a well-established theoretical basi
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Wang, Meng, Stephane Moreau, Gianluca Iaccarino, and Michel Roger. "LES Prediction of Wall-Pressure Fluctuations and Noise of a Low-Speed Airfoil." International Journal of Aeroacoustics 8, no. 3 (2009): 177–97. http://dx.doi.org/10.1260/147547208786940017.

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This paper discusses the prediction of wall-pressure fluctuations and noise of a low-speed flow past a thin cambered airfoil using large-eddy simulation (LES). The results are compared with experimental measurements made in an open-jet anechoic wind-tunnel at Ecole Centrale de Lyon. To account for the effect of the jet on airfoil loading, a Reynolds-averaged Navier-Stokes calculation is first conducted in the full wind-tunnel configuration, and the mean velocities from this calculation are used to define the boundary conditions for the LES in a smaller domain within the potential core of the j
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Shi, Xing, Xianwen Huang, Yao Zheng, and Susu Zhao. "Effects of cambers on gliding and hovering performance of corrugated dragonfly airfoils." International Journal of Numerical Methods for Heat & Fluid Flow 26, no. 3/4 (2016): 1092–120. http://dx.doi.org/10.1108/hff-10-2015-0414.

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Purpose – The purpose of this paper is to explore the effects of the camber on gliding and hovering performance of two-dimensional corrugated airfoils. While the flying mechanism of natural flyers remains a myth up to nowadays, the simulation serves as a minor step toward understanding the steady and unsteady aerodynamics of the dragonfly flight. Design/methodology/approach – The lattice Boltzmann method is used to simulate the flow past the cambered corrugated dragonfly airfoil at low Reynolds numbers. For gliding flight, the maximum camber, the distance of the location of maximum camber poin
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Maleki Dastjerdi, Sajad, Kobra Gharali, Armughan Al-Haq, and Jatin Nathwani. "Application of Simultaneous Symmetric and Cambered Airfoils in Novel Vertical Axis Wind Turbines." Applied Sciences 11, no. 17 (2021): 8011. http://dx.doi.org/10.3390/app11178011.

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Two novel four-blade H-darrieus vertical axis wind turbines (VAWTs) have been proposed for enhancing self-start capability and power production. The two different airfoil types for the turbines are assessed: a cambered S815 airfoil and a symmetric NACA0018 airfoil. For the first novel wind turbine configuration, the Non-Similar Airfoils 1 (NSA-1), two NACA0018 airfoils, and two S815 airfoils are opposite to each other. For the second novel configuration (NSA-2), each of the S815 airfoils is opposite to one NACA0018 airfoil. Using computational fluid dynamics (CFD) simulations, static and dynam
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Liao, Yan Ping, Li Liu, and Teng Long. "Investigation of Various Parametric Geometry Representation Methods for Airfoils." Applied Mechanics and Materials 110-116 (October 2011): 3040–46. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.3040.

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Abstract—This paper presents the investigation of typical parametric geometry representation methods for airfoils, namely, PARSEC method, orthogonal basis function method and CST method. The investigation assesses the fitting accuracy of these parametric methods for various airfoils including the symmetric airfoil, cambered airfoil and supercritical airfoil. The design variables of these parametric methods are solved by the methods of least squares fit. The fitting results show that the fitting accuracy of CST method is better than other parametric methods for airfoil. The aerodynamics analysi
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Désert, T., JM Moschetta, and H. Bézard. "Numerical and experimental investigation of an airfoil design for a Martian micro rotorcraft." International Journal of Micro Air Vehicles 10, no. 3 (2018): 262–72. http://dx.doi.org/10.1177/1756829318794171.

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The present paper aims at investigating the impact of an airfoil design on the propulsion system for a Martian rotary wing micro air vehicle. The main challenge for flying on Mars is the atmosphere’s density and speed of sound that are significantly lower than on Earth. It leads to compressible ultra-low Reynolds number ([Formula: see text]) flows for a coaxial rotorcraft with a 30 cm diameter . Since those flows are unknown in the biosphere, numerical tools have not been validated yet. Therefore, the test section from a known depressurized experiment is simulated in 3D for solver assessment.
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Gao, Ji, Rui Shan Yuan, Ming Hui Zhang, and Yong Hui Xie. "Numerical Study on Thrust Generation Performance of Plunging Airfoils." Applied Mechanics and Materials 312 (February 2013): 235–38. http://dx.doi.org/10.4028/www.scientific.net/amm.312.235.

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In this paper, the effects of angle of attack, camber and camber location on propulsion performance of flapping airfoils undergoing plunging motion were numerically studied at Re=20000 and h=0.175. The unsteady incompressible viscous flow around four different airfoil sections was simulated applying the dynamic mesh. The results show that the time averaged thrust coefficient CTmean and propulsive efficiency η of the symmetric airfoil decrease with the increasing angle of attack, and the variation of CTmean is more obvious than that of CPmean. Both CTmean and η for NACA airfoils studied in this
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Sunada, Shigeru, Akitoshi Sakaguchi, and Keiji Kawachi. "Airfoil Section Characteristics at a Low Reynolds Number." Journal of Fluids Engineering 119, no. 1 (1997): 129–35. http://dx.doi.org/10.1115/1.2819098.

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The aerodynamic characteristics of airfoils operating at Re = 4 × 103 were examined, varying the parameters related to the airfoil shape such as thickness, camber, and roughness. Airfoils with good aerodynamic performance at this Re have the following shape characteristics: (1) they are thinner than airfoils for higher Re numbers, (2) they have a sharp leading edge, and (3) they have a camber of about five percent with its maximum camber at about mid-chord. The characteristics of airfoils are strongly affected by leading edge vortices. The measured two-dimensional airfoil characteristics indic
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Knight, Jason, Simon Fels, Benjamin Beazley, George Haritos, and Andrew Lewis. "Fluid–Structure Interaction of Symmetrical and Cambered Spring-Mounted Wings Using Various Spring Preloads and Pivot Point Locations." Applied Mechanics 2, no. 3 (2021): 591–612. http://dx.doi.org/10.3390/applmech2030034.

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The fluid–structure interaction of a pivoting rigid wing connected to a spring and subjected to freestream airflow in a wind tunnel is presented. Fluid–structure interactions can, on the one hand, lead to undesirable aerodynamic behaviour or, in extreme cases, to structural failure. On the other hand, improved aerodynamic performance can be achieved if a controlled application within certain limitations is provided. One application is the reduction of drag of road vehicles at higher speeds on a straight, while maintaining downforce at lower speeds during cornering. Conversely, another applicat
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Cole, Julian D., and Norman D. Malmuth. "Wave drag due to lift for transonic airplanes." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 461, no. 2054 (2005): 541–60. http://dx.doi.org/10.1098/rspa.2004.1376.

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Lift–dominated pointed aircraft configurations are considered in the transonic range. To make the approximations more transparent, two–dimensionally cambered untwisted lifting wings of zero thickness with aspect ratio of order one are treated. An inner expansion, which starts as Jones's theory, is matched to a nonlinear outer transonic theory as in Cheng and Barnwell's earlier work. To clarify issues, minimize ad hoc assumptions existing in earlier studies, as well as provide a systematic expansion scheme, a deductive rather than inductive approach is used with the aid of intermediate limits a
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Dissertations / Theses on the topic "Thin Cambered Airfoil"

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Gustafson, Eric Andrew. "Design, Simulation, and Wind Tunnel Verication of a Morphing Airfoil." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/33663.

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The application of smart materials to control the flight dynamics of a Micro Air Vehicle (MAV) has numerous benefits over traditional servomechanisms. Under study is wing morphing achieved through the use of piezoelectric Macro Fiber Composites (MFCs). These devices exhibit low power draw but excellent bandwidth characteristics. This thesis provides a background in the 2D analytical and computer modeling tools and methods needed to design and characterize an MFC-actuated airfoil. A composite airfoil is designed with embedded MFCs in a bimorph configuration. The deflection capabilities under a
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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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Books on the topic "Thin Cambered Airfoil"

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Center, Langley Research, ed. The construction of airfoil pressure models by the bonded plate method: Achievements, current research, technology development and potential applications. National Aeronautics and Space Administration, Langley Research Center, 1985.

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Conference papers on the topic "Thin Cambered Airfoil"

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Auletta, Antonio, Fabrizio De Gregorio, Marco Marrazzo, and Marco Lupo. "A PIV/PSP Joint Experimental Analysis of a Thin, High Cambered Airfoil at Low Reynolds Number." In 25th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-4558.

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Auletta, A., F. De Gregorio, D. Guida, M. Lupo, and M. Marrazzo. "A numerical and experimental study of a thin, high cambered airfoil at a low Reynolds number." In ADVANCES IN FLUID MECHANICS 2008. WIT Press, 2008. http://dx.doi.org/10.2495/afm080181.

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Reid, Michael, and Jeffery Kozak. "Thin/Cambered/Reflexed Airfoil Development for Micro Air Vechhicle Applications at Reynolds Numbers of 60,000 to 100,000." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-6508.

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Reid, Michael, and Jeffrey Kozak. "Thin/Cambered/Reflexed Airfoil Development for Micro Air Vehicle Applications at Reynolds Numbers of 60,000 to 100,000." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-6832.

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Rao, J. S., C. V. Ramakrishnan, K. Gupta, and K. K. Rao. "A Mixed Shell Element for Cambered Helicoidal Blades and Dynamic Stresses due to Aerodynamic Excitation." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-356.

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An eight noded mixed shell element for the vibration analysis of rotating cambered helicoidal blades is presented. The strain displacement relations of Gol den’veizer are used and Reissner’s functional is adopted in deriving this element. The effect of initial in-plane stresses is also included. Also, expressions for the pressure difference between the pressure and suction profiles of the rotating blade are derived from two dimensional thin airfoil theories of a stage. The forces thus obtained are applied on the blade to determine the dynamic stresses.
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Gada, Komal, and Hamid Rahai. "Lift and Drag Forces of a High Efficiency Airfoil With an Embedded Rotating Cylinder." In ASME 2016 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/imece2016-66177.

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Numerical investigations of an optimized thin airfoil with an active flow control device (rotating cylinder) embedded into the airfoil have been performed. The objective of the study was to investigate the possibility of using a rotating cylinder to maintain performance of micro aerial vehicles, MAVs, when significant and sudden variation in wind speed (example: gust) is present. The airfoil has a chord length of 19.66 cm and a span of 25 cm. The free stream mean velocity was 20 m/s which corresponds to a chord length Reynolds number of 2.54×105. Simulations were performed at 17 degrees angle
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Bianchini, Alessandro, Francesco Balduzzi, Giovanni Ferrara, and Lorenzo Ferrari. "Aerodynamics of Darrieus Wind Turbines Airfoils During Start-Up." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57679.

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Recent studies have demonstrated that, when rotating around an axis orthogonal to the flow direction, airfoils are virtually transformed into equivalent airfoils with a camber line defined by their arc of rotation. In these conditions, the symmetric airfoils commonly used for Darrieus blades actually behaves like virtually cambered ones or, equivalently, rotors have to be manufactured with counter-cambered blades in order to have the performance of a symmetric airfoil. To complete these analyses, the present study focuses the attention on the airfoils’ aerodynamics during the start-up of the r
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Ligrani, Phil, and Jae Sik Jin. "Second Law Analysis of Aerodynamic Losses: Results for a Cambered Vane With and Without Film Cooling." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-70021.

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Results of second law analysis of experimentally-measured aerodynamic losses are presented for a cambered vane with and without film cooling, including comparisons with similar results from a symmetric airfoil. Included are distributions of local entropy creation, as well as mass-averaged magnitudes of global exergy destruction. The axial chord length of the cambered vane is 4.85 cm, the true chord length is 7.27 cm, and the effective pitch is 6.35 cm. Data are presented for three airfoil Mex distributions (including one wherein the flow is transonic), magnitudes of inlet turbulence intensity
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Bianchini, Alessandro, Francesco Balduzzi, John M. Rainbird, et al. "An Experimental and Numerical Assessment of Airfoil Polars for Use in Darrieus Wind Turbines: Part 1 — Flow Curvature Effects." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42284.

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A better comprehension of the aerodynamic behavior of rotating airfoils in Darrieus Vertical-axis wind turbines (VAWTs) is crucial both for the further development of these machines and for improvement of conventional design tools based on zero or one-dimensional models (e.g. BEM models). When smaller rotors are designed with high chord-to-radius (c/R) ratios so as not to limit the blade Reynolds number, the performance of turbine blades has been suggested to be heavily impacted by a virtual camber effect imparted on the blades by the curvilinear flow they experience. To assess the impact of t
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Bianchini, Alessandro, Francesco Balduzzi, John M. Rainbird, et al. "An Experimental and Numerical Assessment of Airfoil Polars for Use in Darrieus Wind Turbines: Part 2 — Post-Stall Data Extrapolation Methods." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42285.

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Accurate post-stall airfoil data extending to a full range of incidences between −180° to +180° is important to the analysis of Darrieus vertical-axis wind turbines (VAWTs) since the blades experience a wide range of angles of attack, particularly at the low tip-speed ratios encountered during startup. Due to the scarcity of existing data extending much past stall, and the difficulties associated with obtaining post-stall data by experimental or numerical means, wide use is made of simple models of post-stall lift and drag coefficients in wind turbine modeling (through, for example, BEM codes)
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Reports on the topic "Thin Cambered Airfoil"

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Allen, Luke, Joon Lim, Robert Haehnel, and Ian Dettwiller. Helicopter rotor blade multiple-section optimization with performance. Engineer Research and Development Center (U.S.), 2021. http://dx.doi.org/10.21079/11681/41031.

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This paper presents advancements in a surrogate-based, rotor blade design optimization framework for improved helicopter performance. The framework builds on previous successes by allowing multiple airfoil sections to designed simultaneously to minimize required rotor power in multiple flight conditions. Rotor power in hover and forward flight, at advance ratio 𝜇 = 0.3, are used as objective functions in a multi-objective genetic algorithm. The framework is constructed using Galaxy Simulation Builder with optimization provided through integration with Dakota. Three independent airfoil sections
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