Relevant bibliographies by topics / Airfoils

Contents

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

Academic literature on the topic 'Airfoils'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Airfoils"

1

Giljarhus, K. E. T., G. S. Shariatpanahi, and O. A. Frøynes. "Computational investigation of the aerodynamic performance of reversible airfoils for a bidirectional tidal turbine." IOP Conference Series: Materials Science and Engineering 1201, no. 1 (November 1, 2021): 012003. http://dx.doi.org/10.1088/1757-899x/1201/1/012003.

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Abstract A reversible airfoil is an airfoil that has equal performance when the flow is reversed. Such airfoils are relevant for many different applications, including use in ventilation fans, helicopter rotors, wind turbines and tidal turbines. Compared to traditional airfoils, reversible airfoils have different performance characteristics and have been less explored in the scientific literature. This work investigates the aerodynamic performance of some selected reversible airfoils using computational fluid dynamics. The selected airfoils are based on existing NACA 6 profiles and a profile using B-spline parameterization. The results show reduced performance for the reversible airfoils compared to a unidirectional airfoil. Of the investigated airfoils, the B-spline airfoil has the highest performance, with a maximum aerodynamic efficiency which is 87 % of the unidirectional design.
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Chen, Haotian, Yijun Liu, and Yunuo Zhang. "Research on the Aerodynamic Performance of an Airfoil." Journal of Physics: Conference Series 2469, no. 1 (March 1, 2023): 012029. http://dx.doi.org/10.1088/1742-6596/2469/1/012029.

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Abstract Airfoils provide lift force for planes and keep planes flying in the atmosphere. Different airfoils have distinct performance characteristics based on their shapes, influencing the flying condition of planes and people’s safety. Therefore, an airfoil’s shape must be carefully studied and deliberated on because it’s an engineer’s professional duty to protect people’s safety with engineering knowledge. In this paper, physical and mathematical models are applied to analyze the shape and corresponding characteristics of an airfoil. Models, including Bernoulli’s Equation and Ideal gas Law, are applied, which are fundamental engineering models. Professional computational tools, including Matlab, are also utilized for the accuracy of data and plots and convenience in data analysis. As aeronautics technology keeps developing, more challenges will arise. Based on the data of existing airfoils, this paper also brings some considerations for the future of airfoil designs which are going to need to satisfy more flying conditions and types of aircraft.
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Wang, Quan, Boyang Liu, Cong Hu, Fengyun Wang, and Shuyi Yang. "Aerodynamic shape optimization of H-VAWT blade airfoils considering a wide range of angles of attack." International Journal of Low-Carbon Technologies 17 (December 28, 2021): 147–59. http://dx.doi.org/10.1093/ijlct/ctab092.

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Abstract The current H-type vertical axis wind turbine (VAWT) airfoils are from horizontal axis wind turbine airfoils or symmetry airfoils that are designed at one angle of attack (such as α = 6°) rather than different angles of attack. As a consequence, it cannot, to a certain extent, increase wind power efficiency. Therefore, an optimal method of H-type VAWT blade airfoils in different ranges of angles of attack is presented. It can be expressed by airfoil integrated function. Then, an optimized mathematical model in which the objective function is the average of tangential force coefficients is established. The particle swarm optimization algorithm coupled with RFOIL program is introduced to optimize the H-type VAWT airfoil profiles with high aerodynamic performance. The optimized results show that the new HVAWT-00153 airfoil is more suitable to VAWTs than the other two new airfoils and NACA-0015 airfoil. Besides, by using computational fluid dynamics technology, the superiority of HVAWT-00153 airfoil over NCAC-0015 airfoil is reviewed. The results indicate that the H-type VAWT with new HVAWT-00153 airfoils could exhibit larger torque coefficients and higher power coefficients than that of the original H-type VAWT with NACA-0015 airfoils. The maximum power coefficient can reach 0.362, increased by 8.45% compared with that of the original one. This study has a good guidance to how to design the H-type VAWT airfoils with high wind energy power.
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Chen, Xinying, Xinyu Cheng, and Junlu Tian. "Research on the pressure distribution under different airfoil types of aircraft." Journal of Physics: Conference Series 2441, no. 1 (March 1, 2023): 012005. http://dx.doi.org/10.1088/1742-6596/2441/1/012005.

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Abstract Airfoils produce life force for aircraft, which is the reason for planes flying in the sky. The formation of the airfoil depends on its shape, so airfoil designs play an important role in airplane designs. The airfoil design is also prioritized in the process of aircraft design, its speed of creating affecting the progress of the entire project. The goal of airfoil’s design is not simply to create “good” wings, because it does not exist. This means that when airfoils are adapting to a certain airflow or flying condition, their performance might not be satisfied due to environmental variations. Therefore, the application of Computational Fluid Dynamics (CFD) techniques and the Small Disturbance Equation, this study uses python to perform numerical analysis to simulate the surface pressure of the ideal wings under certain flying statues, and then applying a series of algorithms to calculate the shape of the target airfoils, which can find the most suitable airfoil shape under the flying circumstances. According to the researches, the best possible wings satisfying which the pressure below be as larger as possible than the pressure above to produce lift force, is f(x) = k*(x-1)∧4 for downside and f(x) = k*sin(pi(x-1)) for the top. Besides, after a series of calculations, this paper realized that the smaller the k value can be, the better fit it is to an ideal simulated airfoil shape.
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Chen, Ya Qiong, and Yue Fa Fang. "Research on Improved Method of Wind Turbine Airfoil S834 Based on Noise and Aerodynamic Performance." Applied Mechanics and Materials 744-746 (March 2015): 253–58. http://dx.doi.org/10.4028/www.scientific.net/amm.744-746.253.

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In this paper, aerodynamic performance and noise of the wind turbine airfoil are the optimization design goal and based on this, the optimization design method with multi-operating points and multi-objective of the airfoils is built. The Bezier curve is used in parametric modeling of the contour of the airfoil and the general equation for control points is deduced form the discrete points coordinates of the airfoil. The weigh distribution schemes for multi-objective and multi-operating points are integrated designed by treating the NREL S834 airfoil as the initial airfoils. The results show that the lift-to-drag ratio of the optimized airfoils has a improvement around the designed operating angle and the overall noise has a reduction compared with the initial airfoils, which means that the optimized airfoils get a better aerodynamic and acoustic performance.
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Xudong, Wang, Wang Licun, and Xia Hongjun. "An Integrated Method for Designing Airfoils Shapes." Mathematical Problems in Engineering 2015 (2015): 1–12. http://dx.doi.org/10.1155/2015/838674.

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A new method for designing wind turbine airfoils is presented in this paper. As a main component in the design method, airfoil profiles are expressed in a trigonometric series form using conformal transformations and series of polynomial equations. The characteristics of the coefficient parameters in the trigonometric expression for airfoils profiles are first studied. As a direct consequence, three generic airfoil profiles are obtained from the expression. To validate and show the generality of the trigonometric expression, the profiles of the NACA 64418 and S809 airfoils are expressed by the present expression. Using the trigonometric expression for airfoil profiles, a so-called integrated design method is developed for designing wind turbine airfoils. As airfoil shapes are expressed with analytical functions, the airfoil surface can be kept smooth in a high degree. In the optimization step, drag and lift force coefficients are calculated using the XFOIL code. Three new airfoils CQ-A15, CQ-A18, and CQ-A21 with a thickness of 15%, 18%, and 21%, respectively, are designed with the new integrated design method.
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TIAN, WEIJUN, FANGYUAN LIU, QIAN CONG, YURONG LIU, and LUQUAN REN. "STUDY ON AERODYNAMIC PERFORMANCE OF THE BIONIC AIRFOIL BASED ON THE SWALLOW'S WING." Journal of Mechanics in Medicine and Biology 13, no. 06 (December 2013): 1340022. http://dx.doi.org/10.1142/s0219519413400228.

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This paper demonstrates the design of the airfoil of small wind turbines, the bionic airfoil was inspired by the morphology of the swallow's extended wing. The wind tunnel tests on the bionic and standard airfoils NACA4412 were conducted, and the aerodynamic performances of the airfoils were numerically investigated. The results show that the bionic airfoil has better aerodynamic performance, the lift coefficient and lift-drag ratio are larger than those of the NACA4412; with the angle of attack increases, both the bionic and standard airfoils stall, but the stall characteristics of the bionic airfoil are better.
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Zhang, Qing, and Rongrong Xue. "Aerodynamic Exploration of Corrugated Airfoil Based on NACA0030 for Inflatable Wing Structure." Aerospace 10, no. 2 (February 13, 2023): 174. http://dx.doi.org/10.3390/aerospace10020174.

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The flow structures and surface pressure distributions on corrugated airfoils significantly differed from those on a conventional, smooth airfoil. An unsteady, two-dimensional computational simulation was carried out to investigate the flow behavior and associated aerodynamic performance of a group of corrugated airfoils with different levels of waviness at angles of attack from 0° to 20° with an interval of 2° at a low Reynolds number regime (Re = 1.2 × 105) and were quantitatively compared with those of its smooth counterpart. Time-averaged aerodynamic coefficients demonstrated that the corrugated airfoils have a lower lift and higher drag because of trapped vortices in the corrugations. The pressure drag of the corrugated airfoils was greater than that of the smooth airfoil. In contrast, the viscous drag of the corrugated airfoils was smaller than that of the smooth airfoil because the recirculation generated in the corrugation could reduce the viscous drag. The averaged velocity gradient in the boundary layer showed that the thickness of the boundary layer increased significantly for the corrugated airfoils because of recirculating flow caused by the small-standing vortices trapped in the valley of corrugations. The smoother the corrugated surface, the closer the aerodynamic characteristics are to those of the smooth airfoil.
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Zhu, Bao Li, Hui Pen Wu, and Tian Hang Xiao. "Study of Aerodynamic Interactions of Dual Flapping Airfoils in Tandem Configurations." Applied Mechanics and Materials 160 (March 2012): 301–6. http://dx.doi.org/10.4028/www.scientific.net/amm.160.301.

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The unsteady viscous flow fields of dual flapping airfoils in tandem configurations are simulated by a Navier-Stokes Solver based on dynamic deformable hybrid meshes. Aerodynamic interactions of three motion models are studied including flapping fore airfoil with fixed aft airfoil, two airfoils flapping in phase and out-of-phase. The results indicate that the aft airfoil in the wake of the flapping fore airfoil has great influence on the aerodynamic performance. When the fore airfoil flaps with a fixed aft airfoil, the thrust generation and thrust propulsive efficiency were enhanced by 65% and 44% respectively, compared to that of single flapping airfoil. When the two airfoils stoke in phase, the thrust generation is twice over that of single flapping airfoil. However the out-of-phase stroking has relatively much lower thrust.
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Chen, Ya Qiong, Yue Fa Fang, Sheng Guo, and Zhi Hong Chen. "Research on Correction to Fitting Factors of Shape Function and Convergence of Wind Turbine Airfoils." Applied Mechanics and Materials 705 (December 2014): 313–19. http://dx.doi.org/10.4028/www.scientific.net/amm.705.313.

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Based on the functional expression methods of wind turbine airfoils, the method of the correction to parameter factors of shape function by iterative calculation in the principle of making the residual error minimum between the fitting airfoil and the target airfoil is presented in this paper, which makes the fitting precision improved compared with the parametric representation of original airfoils. The method of the correction to parameter factors of shape function proposed in this paper is used for parametric representation of more than 20 kinds of typical airfoils and then the geometric and aerodynamic convergence are intensive studied. The results show that the minimal order of the integrated expression of airfoils is decreased by the proposed method in this paper and the mathematical models of airfoils which facilitate the unification of optimal design are established.
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Dissertations / Theses on the topic "Airfoils"

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Mahmoud, Osama Mohamed Kamal Mohamed. "Experimental investigation of low speed flow over flapping airfoils and airfoil combinations." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA406240.

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Dissertation (Ph.D. in Aeronautical and Astronautical Engineering)--Naval Postgraduate School, Sept. 2001.
Dissertation supervisor: Platzer, Max F. "September 2001." Includes bibliographical references (p. 171-174). Also available in print.
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Yeung, William Wai-Hung. "Modelling stalled airfoils." Thesis, University of British Columbia, 1990. http://hdl.handle.net/2429/31120.

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The thesis deals with some new applications of the wake source model, a two-dimensional incompressible potential flow model used for bodies experiencing flow separation. The body contour is conformally mapped to a circle, for which the flow problem is solved using source singularities to create free streamlines simulating the separating shear layers. In common with other inviscid theories, it generally requires the pressure in the separated flow region, and the location of separation if boundary-layer controlled. Different mapping sequences and flow models have been constructed for the following five problems, 1. the trailing-edge stall for single element airfoils, 2. flat plates with separation bubbles, 3. separation bubbles upstream of spoilers with downstream wakes, 4. spoiler/slotted flap combinations, at which the spoiler inclination is arbitrary, and 5. two-element airfoils near (trailing-edge) stall. Predictions of pressure distribution are compared with wind tunnel measurements, and good agreement is found in cases 1 and 5. The initial shape of the separation streamlines also appears to be satisfactory. Results in cases 2 and 3 are promising although more work is needed to improve the bubble shapes and their pressure distributions. Partial success has been achieved on spoiler/ slotted flap configurations, depending on the spoiler inclination. For strong wake effect on the flap (e. g. δ = 90° ), the model predicts a very high suction peak over it. Whereas the experimental data resemble a stalled distribution even though flow visualization indicates the flap to be unstalled. This may be related to a limitation of the method, also noted in the separation-bubble problems, that it cannot specify a complete boundary condition on a free streamline. This discrepancy diminishes as the spoiler angle becomes smaller (e. g. δ = 30° ) in the cases of higher incidences so that the wake boundary tugs away from the flap sooner.
Applied Science, Faculty of
Mechanical Engineering, Department of
Graduate
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Knappskog, Håvard. "Nonlinear control of Tethered Airfoils : Path-following control of Tethered Airfoils." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for teknisk kybernetikk, 2011. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-13458.

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This master thesis contains modeling, analysis and control design for atethered airfoil. A path-following controller has been developed and provenlocally asymptotically stable. The guidance law is general, and applicableto other path-following systems. The closed loop system is demonstratedin simulations, where a certain level of robustness is concluded.
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Pope, Orrin Dean. "Aerodynamic Centers of Arbitrary Airfoils." DigitalCommons@USU, 2017. https://digitalcommons.usu.edu/etd/6890.

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The study of designing stable aircraft has been widespread and ongoing since the early days of Orville and Wilbur Wright and their famous Wright Flyer airplane. All aircraft as they fly through the air are subject to minor changes in the forces acting on them. The field of aircraft stability seeks to understand and predict how aircraft will respond to these changes in forces and to design aircraft such that when these forces change the aircraft remains stable. The mathematical equations used to predict aircraft stability rely on knowledge of the location of the aerodynamic center, the point through which aerodynamic forces act on an aircraft. The aerodynamic center of an aircraft is a function of the aerodynamic centers of each individual wing, and the aerodynamic center of each wing is a function of the aerodynamic centers of the individual airfoils from which the wing is made. The ability to more accurately predict the location of the airfoil aerodynamic center corresponds directly to an increase in the accuracy of aircraft stability calculations. The Aerolab at Utah State University has develop new analytic mathematical expressions to describe the location of the airfoil aerodynamic center. These new expressions do not suffer from any of the restrictions, or approximations found in traditional methods, and therefore result in more accurate predictions of airfoil aerodynamic centers and by extension, more accurate aircraft stability predictions.
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Alexandris, Georgios. "Supersonic flow past two oscillating airfoils." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA350226.

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Thesis (M.S. in Applied Physics) Naval Postgraduate School, June 1998.
"June 1998." Thesis advisor(s): Max F. Platzer, James H. Luscombe, S. Weber. Includes bibliographical references (p. 71-72). Also available online.
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Shrewsbury, George D. "Dynamic stall of circulation control airfoils." Diss., Georgia Institute of Technology, 1990. http://hdl.handle.net/1853/12397.

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Neculita, Catalin Silviu. "Unsteady compressible flows past oscillating airfoils." Thesis, McGill University, 2005. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99002.

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This thesis presents new and efficient analytical solutions for the unsteady subsonic compressible flows past rigid and flexible airfoils executing low frequency oscillations. These solutions are obtained using an especially developed method based on velocity singularities associated with the airfoil leading edge and ridges, which define the changes in the airfoil boundary conditions. The velocity singularity method has been initially developed by Mateescu.
Closed form solutions are presented for the unsteady lift and pitching moment coefficients and for the chordwise distribution of the unsteady pressure difference coefficient in the general case of rigid airfoils executing oscillatory pitching rotations and translations, as well as for flexible airfoils executing flexural oscillations.
For the case of incompressible flows, the present solutions were found in excellent agreement with the previous incompressible flow results obtained by Theodorsen, Postel & Leppert and by Mateescu & Abdo.
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Garzón, Víctor E. 1972. "Probabilistic aerothermal design of compressor airfoils." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/16995.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.
Includes bibliographical references (p. 175-183).
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Despite the generally accepted notion that geometric variability is undesirable in turbomachinery airfoils, little is known in detail about its impact on aerothermal compressor performance. In this work, statistical and probabilistic techniques were used to assess the impact of geometric and operating condition uncertainty on axial compressor performance. High-fidelity models of geometric variability were constructed from surface measurements of existing hardware using principal component analysis (PCA). A quasi-two-dimensional cascade analysis code, at the core of a parallel probabilistic analysis framework, was used to assess the impact of uncertainty on aerodynamic performance of compressor rotor airfoils. Three rotor blades with inlet relative Mach numbers of 0.82, 0.90 and 1.25 were considered. Discrepancies between nominal and mean loss (mean-shift) of up to 20% were observed. Loss and turning variability were found to grow linearly with geometric noise amplitude. A probabilistic, gradient-based approach to compressor blade optimization was presented. Probabilistic objectives, constraints and gradients are approximated using low-resolution Monte Carlo sampling. Test airfoils were optimized both deterministically and probabilistically and then analyzed probabilistically to account for geometric variability. Probabilistically redesigned airfoils exhibited reductions in mean loss of up to 25% and in loss variability of as much as 65% from corresponding values for deterministically redesigned airfoils.
(cont.) A probabilistic mean-line multi-stage axial compressor model was used to estimate the impact of geometric variability on overall compressor performance. Probabilistic loss and turning models were exercised on a six-stage compressor model. At realistic levels of geometric variability, the mean polytropic efficiency was found to be upwards of 1% lower than nominal. Compressor simulations using airfoils redesigned probabilistically for minimum loss variability exhibited reductions of 30 to 40% in polytropic efficiency variability and mean shift.
by Victor E. Garzon.
Ph.D.
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Walker, William Paul. "Unsteady Aerodynamics of Deformable Thin Airfoils." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34620.

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Unsteady aerodynamic theories are essential in the analysis of bird and insect flight. The study of these types of locomotion is vital in the development of flapping wing aircraft. This paper uses potential flow aerodynamics to extend the unsteady aerodynamic theory of Theodorsen and Garrick (which is restricted to rigid airfoil motion) to deformable thin airfoils. Frequency-domain lift, pitching moment and thrust expressions are derived for an airfoil undergoing harmonic oscillations and deformation in the form of Chebychev polynomials. The results are validated against the time-domain unsteady aerodynamic theory of Peters. A case study is presented which analyzes several combinations of airfoil motion at different phases and identifies various possibilities for thrust generation using a deformable airfoil.
Master of Science
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Joyce, Richard Kirk. "A method of testing two-dimensional airfoils." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23721.

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Books on the topic "Airfoils"

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Airfoil selection: Understanding and choosing airfoils for light aircraft. [Irvine, CA]: B. Wainfan, 2005.

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Harris, Charles D. NASA supercritical airfoils: a matrix of family-related airfoils. Hampton, Va: Langley Research Center, 1990.

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Selig, Michael S. Airfoils at low speeds. Virginia Beach, Va., USA (1504 Horseshoe Cir., Virginia Beach 23451): H.A. Stokely, 1989.

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Ray, Edward J. CAST-10-2/DOA 2 airfoil studies workshop results ; proceedings of a workshop sponsored by the National Aeronautics and Space Administration and held at NASA Langley Research Center, Hampton, Virginia, September 23-27, 1988. Hampton, Va: Langley Research Center, 1989.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Inverse methods for airfoil design for aeronatuical and turbomachinery applications. Neuilly sur Seine, France: AGARD, 1990.

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Johnson, William G. Pressure distributions from high Reynolds number tests of a Boeing BAC I airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel. Washington: NASA, 1985.

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Johnston, G. W. Nonlinear unsteady airfoil response studies. [S.l.]: [s.n.], 1989.

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United States. National Aeronautics and Space Administration., ed. Oscillating airfoils and their wake. Washington DC: National Aeronautics and Space Administration, 1986.

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Barth, Timothy J. Navier-Stokes computations for exotic airfoils. New York: AIAA, 1985.

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Alexandris, Georgios. Supersonic flow past two oscillating airfoils. Monterey, Calif: Naval Postgraduate School, 1998.

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Book chapters on the topic "Airfoils"

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Horvath, Joan, and Rich Cameron. "Airfoils." In 3D Printed Science Projects, 51–76. Berkeley, CA: Apress, 2016. http://dx.doi.org/10.1007/978-1-4842-1323-0_4.

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Kythe, Prem K. "Airfoils." In Computational Conformal Mapping, 269–94. Boston, MA: Birkhäuser Boston, 1998. http://dx.doi.org/10.1007/978-1-4612-2002-2_11.

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Kythe, Prem K. "Joukowski Airfoils." In Handbook of Conformal Mappings and Applications, 193–206. Boca Raton, Florida : CRC Press, [2019]: Chapman and Hall/CRC, 2019. http://dx.doi.org/10.1201/9781315180236-6.

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Nixon, John. "Wings and Airfoils." In Modern English for Aeronautics and Space Technology, 29–40. München: Carl Hanser Verlag GmbH & Co. KG, 2011. http://dx.doi.org/10.3139/9783446428348.002.

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Kythe, Prem K. "Airfoils and Singularities." In Handbook of Conformal Mappings and Applications, 417–50. Boca Raton, Florida : CRC Press, [2019]: Chapman and Hall/CRC, 2019. http://dx.doi.org/10.1201/9781315180236-13.

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Nixon, M. A., and Joseph Michaels. "Wings and Airfoils." In Modern English for Aeronautics and Space Technology, 21–37. 2nd ed. München: Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.3139/9783446470118.002.

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Sobieczky, Helmut. "Parametric Airfoils and Wings." In Notes on Numerical Fluid Mechanics (NNFM), 71–87. Wiesbaden: Vieweg+Teubner Verlag, 1999. http://dx.doi.org/10.1007/978-3-322-89952-1_4.

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Somers, Dan M. "Subsonic Natural-Laminar-Flow Airfoils." In ICASE/NASA LaRC Series, 143–76. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2872-1_4.

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Kuz’min, Alexander, and Alexey Shilkin. "Transonic Buffet over Symmetric Airfoils." In Computational Fluid Dynamics 2006, 849–54. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-92779-2_134.

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Chattot, J. J., and M. M. Hafez. "Inviscid, Unsteady Flows Past Airfoils." In Theoretical and Applied Aerodynamics, 135–53. Dordrecht: Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9825-9_5.

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Conference papers on the topic "Airfoils"

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Kamenická, Daniela, and Martin Bugaj. "Aerodynamic airfoils and their applications." In Práce a štúdie. University of Žilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.1.10.

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This work focuses on aerodynamic airfoils and their application. The significant aim of this work is to introduce and analyse different types of airfoils and their importance. The first part of the paper examines aerodynamic characteristics, airfoil geometry and brings the historical evolution of certain types of airfoils. The second part of the paper considers different databases, and closely examines the NACA database and its numerical labelling by looking at digit series label, which follows the acronym NACA, indicating the airfoil's shape. The main body of the paperillustrates the real-life application of chosen airfoils by examining horizontal and vertical stabilisers and wind turbines. The last part of the paperpresents the analysis of the application of chosen wing root and wingtip airfoils.
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Thwapiah, Ghalib Y., and Flavio L. Campanile. "Nonlinear Aeroelastic Behaviour of Compliant Airfoils." In ASME 2009 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2009. http://dx.doi.org/10.1115/smasis2009-1304.

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Since begin of the aviation and up to the present times, airfoils have always been built as rigid structures. They are designed to fly under their divergence speed in order to avoid static aeroelastic instabilities and the resulting large deformations which are not compatible with the typically low compliance of such airfoils. In recent years, research on airfoil morphing has generated interest in innovative ideas like the use of compliant systems, i.e. systems built to allow for large deformations without failure, in airfoil construction. Such systems can operate in the neighbourhood of divergence and take advantage of large aeroelastic servo-effects. This, in turn, could allow compact, advanced actuators to control the airfoil’s deformation and loads, and hence complement or even replace conventional flaps. In order to analyze and design such compliant, active aeroelastic structures a non-linear approach to static aeroelastic is needed, which takes into account the effect of large deformations on aerodynamics and structure. Such an analytical approach is presented in this paper and applied to a compliant passive airfoil as the preliminary step to the realisation of a piezoelectrically driven, active aeroelastic airfoil. Wind-tunnel test results are also presented and compared with the analytic prediction. The good agreement and the observed behaviour in the wind tunnel give confidence in the potential of this innovative idea.
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Hosseini, N., M. Tadjfar, and A. Abba. "Numerical Study of Aerodynamic Forces of Two Airfoils in Tandem Configuration at Low Reynolds Number." In ASME 2021 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/fedsm2021-65301.

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Abstract For a tandem airfoil configuration, an airfoil is placed in the wake of an upstream airfoil. This interaction affects the aerodynamic forces of the airfoils, especially the downstream one. In the present study a tandem configuration consists of an upstream pitching airfoil and a downstream stationary airfoil is investigated. This study aims to investigate the role of reduced frequency and pitch amplitude of the upstream airfoil’s motion on lift and drag coefficients of two airfoils. These two parameters play an important role in the formation of vortices. The investigation is done for Selig-Donovan 7003 (SD7003) airfoils at low Reynolds number of 30,000 using a computational fluid dynamics. Incompressible URANS equations were employed for solving the flow field. It was found that for a fixed reduced frequency of 0.5 thrust is produced on the hindfoil for a part of cycle for different pitch amplitudes from light to deep stall while for a fixed pitch amplitude at different reduced frequencies high level of thrust or drag can be produced. The reason is related to the type and intensity of vortex-blade interaction.
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Mayda, E. A., C. P. van Dam, and Earl P. N. Duque. "Bubble Induced Unsteadiness on Wind Turbine Airfoils." In ASME 2002 Wind Energy Symposium. ASMEDC, 2002. http://dx.doi.org/10.1115/wind2002-33.

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The effect of laminar separation bubbles on the surface pressure distribution and aerodynamic force characteristics of two quite different airfoils is studied numerically. The low-Reynolds-number Eppler E387 airfoil is analyzed at a chord Reynolds number of 1.0×105 whereas the NREL S809 airfoil for horizontal-axis wind turbines is analyzed at 1.0×106. For all cases in the present study, bubble induced vortex shedding is observed. This flow phenomenon causes significant oscillations in the airfoil surface pressures and, hence, airfoil generated aerodynamic forces. The computed time-averaged pressures compare favorably with wind-tunnel measurements for both airfoils.
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Bianchini, Alessandro, Francesco Balduzzi, John M. Rainbird, Joaquim Peiro, J. Michael R. Graham, Giovanni Ferrara, and Lorenzo Ferrari. "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 this virtual camber effect on blade and turbine performance, a standard NACA0018 airfoil and a NACA0018 conformally transformed such that the airfoil’s chord line follows the arc of a circle, where the ratio of the airfoil’s chord to the circle’s radius is 0.25 were considered. For both airfoils, wind tunnel tests were carried out to assess their aerodynamic lift and drag coefficients for Reynolds numbers of interest for Darrieus VAWTs. Unsteady CFD calculations have been then carried out to obtain curvilinear flow performance data for the same airfoils mounted on a Darrieus rotor with a c/R of 0.25. The blade incidence and lift and drag forces were extracted from the CFD output using a novel incidence angle deduction technique. According to virtual camber theory, the transformed airfoil in this curvilinear flow should be equivalent to the NACA0018 in rectilinear flow, while the NACA0018 should be equivalent to the inverted transformed airfoil in rectilinear flow. Comparisons were made between these airfoil pairings using the CFD output and the rectilinear performance data obtained from the wind tunnel tests and XFoil output in the form of pressure distributions and lift and drag polars. Blade torque coefficients and turbine power coefficient are also presented for the CFD VAWT using both blade profiles.
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Graham, Henry Z., Chad Panther, Meagan Hubbell, Jay P. Wilhelm, Gerald M. Angle, and James E. Smith. "Airfoil Selection for a Straight Bladed Circulation Controlled Vertical Axis Wind Turbine." In ASME 2009 3rd International Conference on Energy Sustainability collocated with the Heat Transfer and InterPACK09 Conferences. ASMEDC, 2009. http://dx.doi.org/10.1115/es2009-90343.

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A vertical axis wind turbine (VAWT) prototype is being developed at West Virginia University that utilizes circulation control to enhance its performance. An airfoil was chosen for this turbine based on its performance potential, and ability to incorporate circulation control. The selection process for the airfoil involved the consideration of camber, blade thickness, and trailing edge radius and the corresponding impact on the lift and drag coefficients. The airfoil showing the highest lift/drag ratio augmentation, compared to the corresponding unmodified airfoil was determined to be the most likely shape for use on the circulation control augmented vertical axis wind turbine. The airfoils selected for this initial investigation were the NACA0018, NACA2418, 18% thick elliptical, NACA0021, and the SNLA2150. The airfoils were compared using the computational fluid dynamics program FLUENT v.6.3.26 with a blowing coefficient of 1% [1]. The size of the trailing edge radius and the slot heights were varied based on past experimental data [2]. The three trailing edge radii and two blowing slot heights were investigated. The thickness of the airfoil impacts the circulation control performance [3], thus it was studied by scaling the NACA0018 to a 21% thickness and compared to an SNLA2150 airfoil. The airfoils’ lift and drag coefficients were compared to determine the most improved lift-drag ratio (L/D). When comparing the increases of the L/D due to circulation control, the NACA0018 and 2418 airfoils were found to outperform the elliptical airfoil; the NACA0018 performed slightly better than the 2418 when comparing the same ratio L/D. The results showed that the 21% thick airfoils produced a decreased L/D profile compared to the NACA0018 airfoils. Therefore, the NACA0018 was found to be the optimal airfoil based from this initial investigation due to an increased L/D compared to the other airfoils tested.
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Timmer, W. A., and R. P. J. O. M. van Rooij. "Summary of the Delft University Wind Turbine Dedicated Airfoils." In ASME 2003 Wind Energy Symposium. ASMEDC, 2003. http://dx.doi.org/10.1115/wind2003-352.

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This paper gives an overview of the design and wind tunnel test results of the wind turbine dedicated airfoils developed by Delft University of Technology (DUT). The DU-airfoils range in maximum relative thickness from 15% to 40% chord. The first designs were made with XFOIL. Since 1995 RFOIL was used, a modified version of XFOIL, featuring an improved prediction around the maximum lift coefficient and capabilities of predicting the effect of rotation on airfoil characteristics. The measured effect of Gurney flaps, trailing edge wedges, vortex generators and trip wires on the airfoil characteristics of various DU-airfoils is presented. Furthermore, a relation between the thickness of the airfoil leading edge and the angle-of-attack for leading edge separation is given.
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Saeed, Farooq, and Michael Selig. "A multipoint inverse airfoil design method for slot-suction airfoils." In 13th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1857.

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Silisteanu, Paul, and Ruxandra Botez. "Two-dimensional airfoil shape optimization for airfoils at low speeds." In AIAA Modeling and Simulation Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4790.

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Pern, Nan, and J. Jacob. "Wake vortex mitigation using adaptive airfoils - The piezoelectric arc airfoil." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-524.

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Reports on the topic "Airfoils"

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Somers, Dan M. Some New Airfoils for Rotorcraft. Fort Belvoir, VA: Defense Technical Information Center, August 2010. http://dx.doi.org/10.21236/ada532301.

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Somers, Dan M. The S415 and S418 Airfoils. Fort Belvoir, VA: Defense Technical Information Center, August 2010. http://dx.doi.org/10.21236/ada545823.

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Somers, D. M. S825 and S826 Airfoils: 1994--1995. Office of Scientific and Technical Information (OSTI), January 2005. http://dx.doi.org/10.2172/15011671.

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Kielb, Robert E., Kenneth C. Hall, Meredith Spiker, Jeffrey P. Thomas, Jr Pratt, Jeffries Edmund T., and Rhett. Non-Synchronous Vibration of Turbomachinery Airfoils. Fort Belvoir, VA: Defense Technical Information Center, March 2006. http://dx.doi.org/10.21236/ada453505.

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Somers, Dan M. The S411, S412, and S413 Airfoils. Fort Belvoir, VA: Defense Technical Information Center, August 2010. http://dx.doi.org/10.21236/ada532303.

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Somers, Dan M. The S407, S409, and S410 Airfoils. Fort Belvoir, VA: Defense Technical Information Center, August 2010. http://dx.doi.org/10.21236/ada532505.

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Kahn, Daniel L., C. P. van Dam, and Dale E. Berg. Trailing edge modifications for flatback airfoils. Office of Scientific and Technical Information (OSTI), March 2008. http://dx.doi.org/10.2172/932882.

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Freymuth, P., R. Tarasewicz, and W. Bank. Vortex Patterns Behind Airfoils in Streamwise Oscillation. Fort Belvoir, VA: Defense Technical Information Center, November 1989. http://dx.doi.org/10.21236/ada229883.

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Leylek, James H., D. K. Walters, William D. York, D. S. Holloway, and Jeffrey D. Ferguson. Computational Film Cooling Methods for Gas Turbine Airfoils. Fort Belvoir, VA: Defense Technical Information Center, March 2002. http://dx.doi.org/10.21236/ada400186.

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Somers, D. M. S822 and S823 Airfoils: October 1992--December 1993. Office of Scientific and Technical Information (OSTI), January 2005. http://dx.doi.org/10.2172/15011666.

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