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.
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TL;DR: In this paper, the simulation of the interaction of two-dimensional incompressible viscous flow and a vibrating airfoil is considered, and the numerical simulation consists of the finite element solution of the Navier-Stokes equations, coupled with the system of ordinary differential equations describing the air-foil motion.
83 citations
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05 Apr 2006TL;DR: A turbofan (14,70) as mentioned in this paper includes a row of fan blades (32) extending from a supporting disk (34) inside an annular casing (16), each blade includes an airfoil (36) having opposite pressure and suction sides (42,44) extending radially in span between a root and tip (46) and axially in chord between leading and trailing edges (48,50).
Abstract: A turbofan (14,70) includes a row of fan blades (32) extending from a supporting disk (34) inside an annular casing (16). Each blade (32) includes an airfoil (36) having opposite pressure and suction sides (42,44) extending radially in span between a root and tip (46) and axially in chord between leading and trailing edges (48,50). Adjacent airfoils (36) define corresponding flow passages (52) therebetween for pressurizing air. Each airfoil (36) includes stagger increasing between the root and tip (46), and the flow passage (52) has a mouth (54) between the airfoil leading edge (48) and the suction side (44) of an adjacent airfoil and converges to a throat (56) aft from the mouth (54). The row includes no more than twenty fan blades (32) having low tip solidity for increasing the width of the passage throat (56).
82 citations
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82 citations
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10 Jan 1994TL;DR: In this article, four different turbulence models are used to compute the flow over a three-element airfoil configuration, including the Baldwin-Barth model, the Spalart-Allmaras model, a two-equation k-omega model, and a new Durbin-Mansour model.
Abstract: Four different turbulence models are used to compute the flow over a three-element airfoil configuration. These models are the one-equation Baldwin-Barth model, the one-equation Spalart-Allmaras model, a two-equation k-omega model, and a new one-equation Durbin-Mansour model. The flow is computed using the INS2D two-dimensional incompressible Navier-Stokes solver. An overset Chimera grid approach is utilized. Grid resolution tests are presented, and manual solution-adaptation of the grid was performed. The performance of each of the models is evaluated for test cases involving different angles-of-attack, Reynolds numbers, and flap riggings. The resulting surface pressure coefficients, skin friction, velocity profiles, and lift, drag, and moment coefficients are compared with experimental data. The models produce very similar results in most cases. Excellent agreement between computational and experimental surface pressures was observed, but only moderately good agreement was seen in the velocity profile data. In general, the difference between the predictions of the different models was less than the difference between the computational and experimental data.
82 citations
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TL;DR: In this paper, a NACA 0015 airfoil with and without a Gurney flap was studied in a wind tunnel with Re c = 2.0 × 105 and Re c ≥ 0.13.
Abstract: A NACA 0015 airfoil with and without a Gurney flap was studied in a wind tunnel with Re
c = 2.0 × 105 in order to examine the evolving flow structure of the wake through time-resolved PIV and to correlate this structure with time-averaged measurements of the lift coefficient. The Gurney flap, a tab of small length (1–4% of the airfoil chord) that protrudes perpendicular to the chord at the trailing edge, yields a significant and relatively constant lift increment through the linear range of the C
L
versus α curve. Two distinct vortex shedding modes were found to exist and interact in the wake downstream of flapped airfoils. The dominant mode resembles a Karman vortex street shedding behind an asymmetric bluff body. The second mode, which was caused by the intermittent shedding of fluid recirculating in the cavity upstream of the flap, becomes more coherent with increasing angle of attack. For a 4% Gurney flap at α = 8°, the first and second modes corresponded with Strouhal numbers based on flap height of 0.18 and 0.13. Comparison of flow around ‘filled’ and ‘open’ flap configurations suggested that the second shedding mode was responsible for a significant portion of the overall lift increment.
82 citations