HAWT dynamic stall response asymmetries under yawed flow conditions

Schreck, S.; Robinson, Michael C.; Hand, M.; Simms, D.

doi:10.2514/6.2000-40

Cited by 18 publications

(4 citation statements)

References 24 publications

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“…10), when the mean angle of attack of the model is 18 • , the solid blockage increases. Due to the existence of the separated flow over the large portion of the airfoil surface, vortices are shed behind the airfoil and the floor pressure port numbers (4), (5), and (6) are influenced by the model motion and the wake vortex shedding. At lower reduced frequency ( Fig.…”

Section: Wall Interference Effectsmentioning

confidence: 99%

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Soltani

Marzabadi

Mohammadi

2011

Experimental Techniques

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A series of experiments were carried out to investigate unsteady behavior of the flow field as well as the boundary layer of an airfoil oscillating in plunging‐type motion in a subsonic wind tunnel. The measurements involved surface‐mounted hot films complimented with surface pressure. In addition, wind tunnel wall pressure distribution was acquired to furnish a baseline for the wall interference corrections. The airfoil is the section of a 660‐kW wind turbine blade. The experiments were conducted at a Reynolds number of 0.42 million, and over two reduced frequencies of k = 0.06 and 0.085, at prestall, nearstall, and poststall regions. The unsteady aerodynamic loads were calculated from the surface pressure measurements, 64 ports, along the chord for both upper and lower surfaces of the model. The plunging displacements were transformed into the equivalent angle of attack. The surface hot‐film measurements provided information about the boundary‐layer events. The boundary‐layer transition occurred via a laminar separation bubble. Variations of the surface pressure coefficients and aerodynamic loads with the equivalent angle of attack showed strong sensitivity to the reduced frequency and the mean angles of attack. The wall pressure distribution was affected by the model oscillation especially the region underneath the model.

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Section: Wall Interference Effectsmentioning

confidence: 99%

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Soltani

Marzabadi

Mohammadi

2011

Experimental Techniques

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“…These reports touch upon the relevant research carried out by the participants in the tasks and they include extensive literature lists. A large part of these lists are added to this article, where the references Shipley, Miller, Robinson, Luttges, and Simms (1994), Hansen (1999), van Rooij, Timmer, and Bruining (2002), Acker and Hand (1999), Bermudez, Velasquez, and Matesanz (2000), Bjorck (1995), Bruining (1993), Chaviaropoulos et al (2001), Duque, van Dam, andHughes (1999), Feigl (2003), Brown, 2000, Leclerc andMasson (1999), Schepers (2011), Miller et al (1995), , Schepers, Feigl, Van Rooij, and Bruining (2004), Schepers and van , Schreck, Robinson, Hand, and Simms (2000), Simms, Robinson, Hand, and Fingersh (1996), Snel (1997), Strzelczyk (1998Strzelczyk ( , 2000, van Rooij (2001van Rooij ( , 2003, van Rooij, Bruining, and Schepers (2003), and van Rooij and Schepers (2005) are related to IEA tasks 14/18. The references Haans, Sant, , Elgammi (2016), Guntur, Sørensen, andSchreck (2013), Hand et al (2001), Kuik, van Rooij, and Imamura (2004), Larwood and Chow (2016), Lindenburg (2003), Meng and van Rooij (2007), Rooij and van Arens (2007), Sant (2007), Sant et al (2006), Schepers (2007aSchepers ( , 2007bSchepers ( , 2007c, Schreck and Robinson (2002), Schreck, Robinso...…”

Section: Literature On Aerodynamic Wind Turbine Measurementsmentioning

confidence: 99%

“…The presence of this vortex and its convection is studied through the analysis of the surface pressure history at the different pressure taps along the chord. Research along these lines initially was carried out using UAE Phase IV surface pressure data, which were acquired in the atmosphere (Schreck et al, 2000) Though wind inflow variations introduced significant anomalies, dynamic stall vortex kinematics were successfully isolated and characterized for yawed rotor conditions, showing pronounced 3D deformations. These unique vortex kinematics were shown to be closely linked to unsteady force amplifications that varied cyclically with blade rotation.…”

Section: Aerodynamic Understandingmentioning

confidence: 99%

Aerodynamic measurements on wind turbines

Schepers

Schreck

2018

WIREs Energy & Environment

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This article reviews the aerodynamic measurement programs on wind turbines that have been performed in the last decades. It is largely based on results from four projects carried out under auspices of the International Energy Agency (IEA), which are denoted as IEA Tasks 14, 18, 20, and 29. The aim of these projects was to collect and analyze aerodynamic measurements on five field facilities (IEA Tasks 14 and 18), the National Renewable Energy Laboratory Phase VI turbine placed in the large NASA Ames wind tunnel (IEA Task 20), and the Mexico turbine placed in the Large Low Speed Facility of the German Dutch Wind tunnel DNW (IEA Task 29). Other experimental programs with an important aerodynamic content are touched upon as well. Research areas for which these measurements have led to important progress are identified. The progress is illustrated with analyses on these experiments. It is shown that detailed aerodynamic measurements are an absolute necessity for the validation and improvement of wind turbine design codes, where it is also concluded that the amount of measurement data which has been produced until now is still far too limited. This article is categorized under: Wind Power > Science and Materials

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“…[1][2][3][4][5] Recently, dynamically stalled blade flow fields have been investigated in detail, significantly improving comprehension of the three-dimensional vortex dynamics responsible for these flows. [6][7][8] Typically, dynamic stall dominates turbine blade flow fields at large to moderate yaw angles, and remains prominent even under low yaw conditions. However, low yaw angles appreciably attenuate dynamic stall effects, permitting emergence of rotational influences.…”

Section: Introductionmentioning

confidence: 99%

Rotationally Augmented Flow Structures and Time Varying Loads on Turbine Blades

Schreck¹

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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HAWT dynamic stall response asymmetries under yawed flow conditions

Cited by 18 publications

References 24 publications

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Aerodynamic measurements on wind turbines

Rotationally Augmented Flow Structures and Time Varying Loads on Turbine Blades

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