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Topic

Airfoil

About: Airfoil is a research topic. Over the lifetime, 24696 publications have been published within this topic receiving 337709 citations. The topic is also known as: aerofoil & wing section.


Papers
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Journal ArticleDOI
01 Oct 2016-Energy
TL;DR: In this paper, a series of transient CFD simulations were carried out using ANSYS Fluent to evaluate the effects of several geometric attributes of the turbine rotor on the starting characteristics, and the result of this simulation, in the form of an accelerating time series, demonstrates good agreement with the published experimental data, proving its usefulness for similar problems.

96 citations

Journal ArticleDOI
TL;DR: In this article, a 3-kW straight-bladed Darrieus type Vertical Axis Wind Turbine (VAWT) is investigated numerically using OpenFOAM computational fluid dynamic package.

96 citations

Patent
21 Dec 1990
TL;DR: In this paper, an airfoil for a compression section 12 of a rotary machine is described, which has a spanwise axis 52 or stacking line which extends in a generally radial direction.
Abstract: An airfoil for a compression section 12 of a rotary machine 10 is disclosed. Various construction details are developed to increase the efficiency of the compression section 12. In one detailed embodiment, the airfoil has a spanwise axis 52 or stacking line which extends in a generally radial direction. The stacking line or spanwise axis 52 is straight over the mid-section of the airfoil and is angled circumferentially toward the radial direction in the end wall regions 58, 66 of the airfoil.

96 citations

Proceedings ArticleDOI
01 Jan 1992
TL;DR: Results obtained from a second wind tunnel test of the first model in the Benchmark Models Program are described, which consisted of a rigid semispan wing having a rectangular planform and a NACA 0012 airfoil shape which was mounted on a flexible two degree of freedom mount system.
Abstract: The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of this program is to acquire measured dynamic instability and corresponding pressure data that will be useful for developing and evaluating aeroelastic type computational fluid dynamics codes currently in use or under development. The program is a multi-year activity that will involve testing of several different models to investigate various aeroelastic phenomena. This paper describes results obtained from a second wind tunnel test of the first model in the Benchmark Models Program. This first model consisted of a rigid semispan wing having a rectangular planform and a NACA 0012 airfoil shape which was mounted on a flexible two degree of freedom mount system. Experimental flutter boundaries and corresponding unsteady pressure distribution data acquired over two model chords located at the 60 and 95 percent span stations are presented.

95 citations

Journal ArticleDOI
TL;DR: In this paper, a high-resolution particle image velocimetry system was used to quantify the transient behavior of vortex and turbulent flow structures around the flexible-membrane airfoils/wings.
Abstract: An experimental study was conducted to assess the benefits of using flexible-membrane airfoils/wings at low Reynolds numbers for micro air vehicle applications compared with using a conventional rigid airfoil/wing. In addition to measuring aerodynamic forces acting on flexible-membrane airfoils/wings, a high-resolution particle image velocimetry system was used to conduct flowfield measurements to quantify the transient behavior of vortex and turbulent flow structures around the flexible-membrane airfoils/wings to elucidate the associated underlying fundamental physics. The aerodynamic force measurements revealed that flexible-membrane airfoils could provide better aerodynamic performance compared with their rigid counterpart at low Reynolds numbers. The flexibility (or rigidity) of the membrane skins of the airfoils was found to greatly affect their aerodynamic performance. Particle image velocimetry measurements elucidated that flexible-membrane airfoils could change their camber (i.e., crosssectional shape) automatically to adapt incoming flows to balance the pressure differences on the upper and lower surfaces of the airfoils, therefore suppressing flow separation on the airfoil upper surfaces. Meanwhile, deformation of the flexible-membrane skins was found to cause significant airfoil trailing-edge deflection (i.e., lift the airfoil trailing edge up from its original designed position), which resulted in a reduction of the effective angles of attack of the flexible-membrane airfoils, thereby delaying airfoil stall at high angles of attack. The nonuniform spanwise deformation of the flexible-membrane skins of the flexible-membrane airfoils was found to significantly affect the characteristics of vortex and turbulent flow structures around the flexible-membrane airfoils.

95 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20231,083
20221,871
2021923
2020979
20191,097
20181,002