HAWT near‐wake aerodynamics, Part I: axial flow conditions

Haans, Wouter; Sant, Tonio; Kuik, Gam Gijs van; Bussel, Gjw Gerard van

doi:10.1002/we.262

Cited by 23 publications

(23 citation statements)

References 20 publications

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“…A NACA0012 profile is used on the lifting part of the blade from r/R=0.3 up to the tip, and the blade has constant chord length of 0.08m with linear twist distribution. Detailed information regarding the wind turbine and the research program of TUDelft can be found in the works of Sant [15] and Haans et al [16]. The blade can be pitched at different angles.…”

Section: Resultsmentioning

confidence: 99%

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Moving actuator surfaces: a new concept for wind turbine aerodynamic analysis

Masson

Sibuet²

2024

RE&PQJ

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The actuator disk is a concept often used in wind turbine aerodynamics, where the action of the turbine on the flow is averaged over time and space. This simplification stills retain sufficient physical information for wind turbine aerodynamic design. Its limitations are essentially related to the impossibility to model the blade shed vorticity. This paper presents a more general approach that uses rotating actuator surfaces carrying velocity and pressure discontinuities which are set from knowledge of the circulation around the model blade sections and using blade element analysis. The mathematics of rotating actuator surfaces, as well as an application to the TUDelft rotor are presented in this paper. The results are encouraging.

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Section: Resultsmentioning

confidence: 99%

“…Several adaptations are necessary to ensure numerical convergence and are presented. Comparisons between numerical results and experimental measurements are presented for the TUDelft experimental rotors [16].…”

Section: Introductionmentioning

confidence: 99%

Moving actuator surfaces: a new concept for wind turbine aerodynamic analysis

Masson

Sibuet²

2024

RE&PQJ

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“…The validation of the free-vortex wake method for a wind turbine in axial flow was performed against the wake geometry measurements obtained by Haans et al 6 . In addition, aerodynamic analysis of NREL Phase VI rotor 7 was…”

Section: Resultsmentioning

confidence: 99%

“…(a) Schematic of the experimental test setup (b) Tip vortex for Λ=0°, λ=8, and θtip=2° Present Experiment [6] Reference [3] a) Tip vortex geometry for θtip= 0° (b) Tip vortex geometry for θtip= 2° (c) Tip vortex geometry for θtip= 4° Fig. 2.…”

Section: Wake Geometry Validation (Haans Et Al Experiment)mentioning

confidence: 99%

“…For these reasons, the aerodynamic loads were computed using the vortex method based on a time-marching free-vortex wake method in this research. The wake geometry validation and aerodynamic responses were compared with Haans et al experiment 6 and unsteady aerodynamics experiment (UAE) 7 in axial flow condition. The numerical responses show excellent agreement with experiments 6, 7 .…”

Section: Introductionmentioning

confidence: 99%

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Wind Turbine Aerodynamics Prediction Using Free-Wake Method in Axial Flow

Jeong

Yoo

Lee

2012

Int. J. Mod. Phys. Conf. Ser.

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Wind turbine aerodynamics remains a particularly challenging and crucial research for wind energy industry. The blade element momentum theory is the most widely used in predicting the performance of wind turbine, since the method is simple and fast numerical algorithm. The flow field generated by rotary wing is considerably important and complicated, however, the BEM method has some limitations to model the unsteady effects. To overcome these limitations, the aerodynamic analysis using a time-marching free-vortex wake method was performed in this paper. Moreover, the inboard region of the blade experience a delay in stall and enhanced values of the normal force coefficient because of rotational boundary layer augmentation and threedimensional effects. For this reason, Raj-Selig stall delay model was applied in this research. The numerical results were compared with experimental data, and the present results show excellent agreement with experiment.

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Modeling of lifting‐device aerodynamics using the actuator surface concept

Watters

Masson

2009

Numerical Methods in Fluids

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The actuator surface (AS) concept and its implementation within a differential, Navier-Stokes control volume finite-element method (CVFEM) are presented in this article. Inspired by vortex and actuator disk methods, the AS concept consists of using porous surfaces carrying velocity and pressure discontinuities to model the action of lifting surfaces on the flow. The underlying principles and mathematics associated with AS are first reviewed, as well as their implementation in a CVFEM. Results are presented for idealized 2D cases with analytical solutions, as well as for the 3D cases of a finite wing and an experimental wind turbine. In the case of the finite wing, wake induction is well handled by the model with accurate predictions of induced angles and drag when compared with the Prandtl lifting line model. Comparisons with volume force approaches, often used to model the action of propellers or wind turbine blades in a simplified analysis, show that the AS concept has some interesting advantages in terms of accuracy and respect of flow physics. This new approach is easy and rapid to embed in most computational fluid dynamics (CFD) methods. It is applicable to a wide range of problems involving thin lifting devices like finite wings, propellers, helicopter or wind turbine blades. THE ACTUATOR SURFACE CONCEPT 1265 and force distributions acting within them is important issues that can strongly influence the flow solution. With regards to fans or propellers, the actuator disk concept introduced by Froude should also be included in this group of simplified models; however, the action of the modeled device is spread over a surface rather than a volume. Volume forces become surface forces and discontinuities occur at the actuator disk surface in flow properties like pressure and velocity (see for example [9]). Inspired by the actuator disk concept, this article proposes the use of a new type of singular surface, called an actuator surface (AS), to represent the action of any lifting surface within a differential Navier-Stokes, control volume (CV) finite-element-based method. An AS is simply a geometric surface carrying velocity and pressure discontinuities, as well as surface forces, which are all determined from the circulation along the lifting sections of the AS. Equivalently, an AS is a porous vortex sheet that represents the bound vorticity system of a lifting device. The flow induced by the AS is solved using a CFD method that has been adapted to account for the kinematic and dynamic influence of the AS. As for volume force approaches, the trailing system of vorticity is naturally modeled by the CFD method. To situate the AS approach, Figure 1 presents a possible classification of models for lifting-device aerodynamics by sketching different approaches to model e.g. a lifting wing. On the left part of the figure, vortex models regroup lifting-line, vortex-lattice and panel models. These models are based on distributions of vorticity singularities whose magnitudes are set either based on kinematic conditions (s...

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HAWT near‐wake aerodynamics, Part I: axial flow conditions

Cited by 23 publications

References 20 publications

Moving actuator surfaces: a new concept for wind turbine aerodynamic analysis

Moving actuator surfaces: a new concept for wind turbine aerodynamic analysis

Wind Turbine Aerodynamics Prediction Using Free-Wake Method in Axial Flow

Modeling of lifting‐device aerodynamics using the actuator surface concept

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