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Relevant bibliographies by topics / Unsteady Airfoil

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Academic literature on the topic 'Unsteady Airfoil'

Author: Grafiati

Published: 4 June 2021

Last updated: 5 February 2022

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Journal articles on the topic "Unsteady Airfoil"

1

Abdessemed, Chawki, Yufeng Yao, Abdessalem Bouferrouk, and Pritesh Narayan. "Morphing airfoils analysis using dynamic meshing." International Journal of Numerical Methods for Heat & Fluid Flow 28, no. 5 (2018): 1117–33. http://dx.doi.org/10.1108/hff-06-2017-0261.

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Purpose The purpose of this paper is to use dynamic meshing to perform CFD analyses of a NACA 0012 airfoil fitted with a morphing trailing edge (TE) flap when it undergoes static and time-dependent morphing. The steady CFD predictions of the original and morphing airfoils are validated against published data. The study also investigates an airfoil with a hinged TE flap for aerodynamic performance comparison. The study further extends to an unsteady CFD analysis of a dynamically morphing TE flap for proof-of-concept and also to realise its potential for future applications. Design/methodology/a

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2

Ho, WH, and TH New. "Unsteady numerical investigation of two different corrugated airfoils." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 13 (2016): 2423–37. http://dx.doi.org/10.1177/0954410016682539.

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An unsteady, two-dimensional numerical study was conducted to investigate the aerodynamic and flow characteristics of two bio-inspired corrugated airfoils at Re = 14,000 and compared with those of a smooth NACA0010 airfoil. Mean aerodynamic results reveal that the corrugated airfoils have better lift performance compared to the NACA0010 airfoil but incur slightly higher drag penalty. Mean flow streamlines indicate that this favourable performance is due to the ability of the corrugated airfoils in mitigating large-scale flow separations and stall. Unsteady flow field results show persistent fo

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3

Buffum, D. H., and S. Fleeter. "Effect of Wind Tunnel Acoustic Modes on Linear Oscillating Cascade Aerodynamics." Journal of Turbomachinery 116, no. 3 (1994): 513–24. http://dx.doi.org/10.1115/1.2929440.

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The aerodynamics of a biconvex airfoil cascade oscillating in torsion is investigated using the unsteady aerodynamic influence coefficient technique. For subsonic flow and reduced frequencies as large as 0.9, airfoil surface unsteady pressures resulting from oscillation of one of the airfoils are measured using flush-mounted high-frequency-response pressure transducers. The influence coefficient data are examined in detail and then used to predict the unsteady aerodynamics of a cascade oscillating at various interblade phase angles. These results are correlated with experimental data obtained

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4

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

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5

Atassi, H. M., J. Fang, and S. Patrick. "Direct Calculation of Sound Radiated From Bodies in Nonuniform Flows." Journal of Fluids Engineering 115, no. 4 (1993): 573–79. http://dx.doi.org/10.1115/1.2910182.

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Sound radiated from a single airfoil and a cascade of airfoils in three-dimensional gusts is directly calculated. Euler’s equations are linearized about the mean flow of the airfoil or cascade. The velocity field is split into a vortical part and a potential part. The latter is governed by a single nonconstant-coefficient convective wave equation. For a single airfoil, the radiated sound is calculated using Kirchhoff’s method from the mid field of the unsteady pressure obtained through the unsteady aerodynamic solver. The results indicate the importance of the contribution of the quadrupole ef

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6

Buffum, D. H., and S. Fleeter. "The Aerodynamics of an Oscillating Cascade in a Compressible Flow Field." Journal of Turbomachinery 112, no. 4 (1990): 759–67. http://dx.doi.org/10.1115/1.2927719.

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Fundamental experiments are performed in the NASA Lewis Research Center Transonic Oscillating Cascade Facility to investigate and quantify the aerodynamics of a cascade of bioconvex airfoils executing torsion mode oscillations at realistic reduced frequency values. Both steady and unsteady airfoil surface pressures are measured at two inlet Mach numbers, 0.65 and 0.80. and two incidence angles, 0 and 7 deg, with the harmonic torsional airfoil cascade oscillations at realistic high reduced frequency and unsteady data obtained at several interbladephase angle values. The time-variant pressures a

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7

Zhu, Chengyong, Tongguang Wang, and Jianghai Wu. "Numerical Investigation of Passive Vortex Generators on a Wind Turbine Airfoil Undergoing Pitch Oscillations." Energies 12, no. 4 (2019): 654. http://dx.doi.org/10.3390/en12040654.

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Passive vortex generators (VGs) are widely used to suppress the flow separation of wind turbine blades, and hence, to improve rotor performance. VGs have been extensively investigated on stationary airfoils; however, their influence on unsteady airfoil flow remains unclear. Thus, we evaluated the unsteady aerodynamic responses of the DU-97-W300 airfoil with and without VGs undergoing pitch oscillations, which is a typical motion of the turbine unsteady operating conditions. The airfoil flow is simulated by numerically solving the unsteady Reynolds-averaged Navier-Stokes equations with fully re

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8

Motta, Valentina, Alberto Guardone, and Giuseppe Quaranta. "Influence of airfoil thickness on unsteady aerodynamic loads on pitching airfoils." Journal of Fluid Mechanics 774 (June 11, 2015): 460–87. http://dx.doi.org/10.1017/jfm.2015.280.

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The influence of the airfoil thickness on aerodynamic loads is investigated numerically for harmonically pitching airfoils at low incidence, under the incompressible and inviscid flow approximation. Force coefficients obtained from finite-volume unsteady simulations of symmetrical 4-digit NACA airfoils are found to depart from the linear Theodorsen model of an oscillating flat plate. In particular, the value of the reduced frequency resulting in the inversion – from clockwise to counter-clockwise – of the lift/angle-of-attack hysteresis curve is found to increase with the airfoil thickness. Bo

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9

Henderson, G. H., and S. Fleeter. "Forcing Function Effects on Unsteady Aerodynamic Gust Response: Part 2—Low Solidity Airfoil Row Response." Journal of Turbomachinery 115, no. 4 (1993): 751–59. http://dx.doi.org/10.1115/1.2929310.

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The fundamental gust modeling assumption is investigated by means of a series of experiments performed in the Purdue Annular Cascade Research Facility. The unsteady periodic flow field is generated by rotating rows of perforated plates and airfoil cascades, with the resulting unsteady periodic chordwise pressure response of a downstream low-solidity stator row determined by miniature pressure transducers embedded within selected airfoils. When the forcing function exhibited the characteristics of a linear-theory vortical gust, as was the case for the perforated-plate wake generators, the resul

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10

Buffum, D. H., and S. Fleeter. "Wind Tunnel Wall Effects in a Linear Oscillating Cascade." Journal of Turbomachinery 115, no. 1 (1993): 147–56. http://dx.doi.org/10.1115/1.2929199.

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Experiments in a linear oscillating cascade reveal that the wind tunnel walls enclosing the airfoils have, in some cases, a detrimental effect on the oscillating cascade aerodynamics. In a subsonic flow field, biconvex airfoils are driven simultaneously in harmonic, torsion-mode oscillations for a range of interblade phase angle values. It is found that the cascade dynamic periodicity—the airfoil-to-airfoil variation in unsteady surface pressure—is good for some values of interblade phase angle but poor for others. Correlation of the unsteady pressure data with oscillating flat plate cascade p

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Dissertations / Theses on the topic "Unsteady Airfoil"

1

Cricelli, Antonio M. "Unsteady airfoil flow solutions on moving zonal grids." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23803.

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2

Scott, Matthew Thomas. "Nonlinear airfoil-wake interaction in large amplitude unsteady flow." Thesis, Massachusetts Institute of Technology, 1987. http://hdl.handle.net/1721.1/14650.

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Poling, David R. "Airfoil response to periodic disturbances: the unsteady Kutta condition." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/76166.

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Unsteady flow fields over a NACA 0012 at an angle of attack are investigated. The first is the classical pitching motion about the airfoil's quarter chord. The second is the flow over a fixed airfoil immersed in the wake of the pitching airfoil. Large reduced frequencies are considered. Measurements were obtained in a water tunnel by Laser-Doppler velocimetry. Ensemble-averaged velocity measurements were obtained in the vicinity of the trailing edges of both the pitching and the fixed airfoils. The flowfields in the wake and at the trailing edges of both airfoils were studied visually. The val

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4

Yeow, Kim Fong. "An experimental investigation High rate/high lift aerodynamics Unsteady airfoil." Ohio University / OhioLINK, 1989. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1182179063.

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Staubs, Joshua Kyle. "Real Airfoil Effects on Leading Edge Noise." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/27911.

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This dissertation presents measurements of the far-field noise associated with the interaction of grid-generated turbulence with a series of airfoils of various chord lengths, thicknesses, and camber. The radiated noise was measured for a number of angles of attack for each airfoil to determine the effects of angle of attack on the leading edge noise. Measurements are compared with numerous theories to determine the mechanism driving the production of leading edge noise. Calculations were also made using a boundary element method to determine the effects of airfoil shape on the unsteady loadin

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6

Price, Jennifer Lou. "Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps." NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010713-170959.

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<p>Price, Jennifer Lou. Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps. (Under the direction of Dr. Ndaona Chokani)The effect of a Gurney flap on an unsteady airfoil flow is experimentally and computationally examined. In the experiment, the details of the unsteady boundary layer events on the forward portion of the airfoil are measured. In the computation, the features of the global unsteady flow are documented and correlated with the experimental observations.The experiments were conducted in the North Carolina State University subsonic wind tunnel on an o

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7

Durand, Eric 1973. "Time domain modeling of unsteady aerodynamic forces on a flapping airfoil." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/47668.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.<br>Includes bibliographical references (p. 69-70).<br>The goal of this research is to develop a versatile and fast code to compute the unsteady lift and thrust forces generated by a flapping airfoil and apply it to engineering problems. We consider both plunging and pitching types of motion and develop a time marching simulation based on early work in unsteady aerodynamics. The ability of the code to compute lift and thrust forces is validated against published results. We then study ways to maxi

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8

Kong, Lingzhe. "Experimental investigation of the tolerant wind tunnel for unsteady airfoil motion testing." Thesis, University of British Columbia, 1991. http://hdl.handle.net/2429/29992.

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Previously, the concept of the tolerant wind tunnel, developed in the Department of Mechanical Engineering, U. B. C., was tested only for stationary models. In the present study, the concept is investigated for unsteady airfoil motion. The new wind tunnel test section, using the opposite effects of solid and open boundaries, is a new approach to reduce wall blockage effects. Consisting of vertical airfoil slats uniformly spaced on both side walls in the test section, it is designed to produce a nearly free-air test environment for the test model, which leads to negligible or small corrections

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9

Castañeda, Vergara David Armando. "Active Control of Flow over an Oscillating NACA 0012 Airfoil." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587420875168203.

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Gornowicz, Galen Gerald Dimotakis Paul E. "Continuous-field image-correlation velocimetry and its application to unsteady flow over an airfoil /." Diss., Pasadena, Calif. : California Institute of Technology, 1997. http://resolver.caltech.edu/CaltechETD:etd-08062004-141142.

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Books on the topic "Unsteady Airfoil"

1

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

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2

Cebeci, Tuncer, Max Platzer, Hsun Chen, Kuo-Cheng Chang, and Jian P. Shao. Analysis of Low-Speed Unsteady Airfoil Flows. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/b138967.

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3

Giles, Michael. Non-reflecting boundary conditions for unsteady airfoil calculations. Massachusetts Institute of Technology, Computational Fluid Dynamics Laboratory, 1990.

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4

Cricelli, Antonio M. Unsteady airfoil flow solutions on moving zonal grids. Naval Postgraduate School, 1992.

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5

Wall, Berend van der. The influence of variable flow velocity on unsteady airfoil behavior. Deutsche Forschungsanstalt für Luft- und Raumfahrt, 1992.

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6

Nakamichi, Jiro. Some computations of unsteady Navier-Stokes flow around oscillating airfoil/wing. National Aerospace Laboratory, 1988.

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7

Srinivasan, G. R. Evaluation of turbulence models for unsteady flows of an oscillating airfoil. Pergamon, 1995.

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8

Ravindran, S. S. Active control of flow separation over an airfoil. National Aeronautics and Space Administration, Langley Research Center, 1999.

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9

Ravindran, S. S. Active control of flow separation over an airfoil. National Aeronautics and Space Administration, Langley Research Center, 1999.

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10

Zdunich, Patrick. A discrete vortex model of unsteady separated flow about a thin airfoil for application to hovering flapping-wing flight. National Library of Canada, 2002.

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Book chapters on the topic "Unsteady Airfoil"

1

Gülçat, Ülgen. "Incompressible Flow About an Airfoil." In Fundamentals of Modern Unsteady Aerodynamics. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14761-6_3.

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2

Gülçat, Ülgen. "Incompressible Flow About an Airfoil." In Fundamentals of Modern Unsteady Aerodynamics. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-60777-7_3.

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3

Gülçat, Ülgen. "Incompressible Flow About an Airfoil." In Fundamentals of Modern Unsteady Aerodynamics. Springer Singapore, 2015. http://dx.doi.org/10.1007/978-981-10-0018-8_3.

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4

Cebeci, Tuncer, Max Platzer, Hsun Chen, Kuo-Cheng Chang, and Jian P. Shao. "Physics of Unsteady Flows." In Analysis of Low-Speed Unsteady Airfoil Flows. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/3-540-27361-1_1.

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5

Morishita, E., H. Koyama, T. Kitamori, and Y. Aihara. "Unsteady Aerodynamic Characteristics of Deformable Airfoil." In Fluid Dynamics of High Angle of Attack. Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52460-8_5.

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6

Frey, Kuk Kim, and Sanford Fleeter. "Rotating Blade Row Oscillating Airfoil Aerodynamics." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines. Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_5.

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7

Tsangaris, S., A. Pentaris, and M. Thomadakis. "Unsteady Flow Over a Circular Arc Airfoil." In Notes on Numerical Fluid Mechanics (NNFM). Vieweg+Teubner Verlag, 1998. http://dx.doi.org/10.1007/978-3-322-89859-3_61.

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8

Lorber, Peter F., and Eugene E. Covert. "Unsteady Airfoil Boundary Layers—Experiment and Computation." In Numerical and Physical Aspects of Aerodynamic Flows III. Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4926-9_14.

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Cebeci, Tuncer, Max Platzer, Hsun Chen, Kuo-Cheng Chang, and Jian P. Shao. "Companion Computer Programs." In Analysis of Low-Speed Unsteady Airfoil Flows. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/3-540-27361-1_10.

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Cebeci, Tuncer, Max Platzer, Hsun Chen, Kuo-Cheng Chang, and Jian P. Shao. "The Differential Equations of Fluid Flow." In Analysis of Low-Speed Unsteady Airfoil Flows. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/3-540-27361-1_2.

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Conference papers on the topic "Unsteady Airfoil"

1

Hermes, Viktor, Igor Klioutchnikov, Atef Alshabu, and Herbert Olivier. "Investigation of Unsteady Transonic Airfoil Flow." In 46th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-627.

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2

Gurbacki, Holly, and Michael Bragg. "Unsteady Flowfield About an Iced Airfoil." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-562.

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3

Kuroda, Shinichi. "Numerical computations of unsteady flows for airfoils and non-airfoil structures." In 15th AIAA Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-2714.

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4

Fuchiwaki, Masaki, Chang Jo Yang, and Kazuhiro Tanaka. "Unsteady Separation and Vortex Around Moving Airfoils." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45192.

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The dynamic behavior of vortices shed from the leading edge of two kinds of pitching airfoils, such as NACA65-0910 and BTE, was visualized by dye flow visualization and schlieren visualization for Re = 4.0 × 103. Moreover, the dynamic lift acting on them was measured by a six-axes sensor in a water tunnel for Re = 4.0 × 104. In case of both airfoils, the reattachment appeared at the higher angle of attack with higher non-dimensional pitching rate. The dynamic behavior of the reattachment depended on the airfoil configuration and the recirculation region was formed by a few discrete vortices. T

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5

Boyd, Douglas. "Unsteady aerodynamic airfoil-to-airfoil variability in an axial flow compressor." In 38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-14.

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Gurbacki, H., and M. Bragg. "Unsteady aerodynamic measurements on an iced airfoil." In 40th AIAA Aerospace Sciences Meeting & Exhibit. American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-241.

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Chiereghin, Nicola, David Cleaver, and Ismet Gursul. "Unsteady Measurements for a Periodically Plunging Airfoil." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0996.

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Gupta, Rohit, and Phillip J. Ansell. "Unsteady Flow Physics of Airfoil Dynamic Stall." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0999.

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Bull, Samuel, Nicola Chiereghin, Ismet Gursul, and David Cleaver. "Unsteady Aerodynamics of a Transient Plunging Airfoil." In 2018 AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0353.

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Fuchiwaki, Masaki, and Kazuhiro Tanaka. "Vortex Flow Behind an Unsteady Airfoil in Pitching and Heaving Motions and Dynamic Thrust." In ASME 2006 2nd Joint U.S.-European Fluids Engineering Summer Meeting Collocated With the 14th International Conference on Nuclear Engineering. ASMEDC, 2006. http://dx.doi.org/10.1115/fedsm2006-98487.

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The detailed vortex flow structure behind a combination airfoil at a low Reynolds number region was measured by PIV. Moreover, the dynamic thrust acting on a combination airfoil was measured by a six-axes sensor in water tunnel. The combination airfoil can form clear thrust producing vortex street behind airfoil even at low non-dimensional trailing edge velocity and non-dimensional heaving velocity. Especially, it is possible to form the thrust producing vortex street with high vorticity at φ = π/2 and π. The jet velocity behind combination airfoil at φ = π/2 and π becomes over 2.0. The averag

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Reports on the topic "Unsteady Airfoil"

1

Ho, Chih-Ming. Manipulation of Airfoil Response in an Unsteady Stream. Defense Technical Information Center, 1996. http://dx.doi.org/10.21236/ada311791.

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2

Covert, Eugene E., Michael J. Fletcher, Kirk J. Flittie, and Samuel W. Linton. On the Unsteady Characteristics of Flows Around an NACA 0012 Airfoil. Defense Technical Information Center, 1986. http://dx.doi.org/10.21236/ada179654.

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You, Donghyun, William Bromby, and Adamandios Sifounakis. Large-Eddy Simulation Analysis of Unsteady Separation Over a Pitching Airfoil at High Reynolds Number. Defense Technical Information Center, 2013. http://dx.doi.org/10.21236/ada608653.

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4

Ayoul-Guilmard, Q., F. Nobile, S. Ganesh, et al. D6.4 Report on stochastic optimisation for unsteady problems. Scipedia, 2021. http://dx.doi.org/10.23967/exaqute.2021.2.003.

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This report brings together methodological research on stochastic optimisation and work on benchmark and target applications of the ExaQute project, with a focus on unsteady problems. A practical, general method for the optimisation of the conditional value at risk is proposed. Three different optimisation problems are described: an oscillator problem selected as a suitable trial and illustration case; the shape optimisation of an airfoil, chosen as a benchmark application in the project; the shape optimisation of a tall building, which is the challenging target application set for ExaQUte. Fo

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