Control of Dynamically Stalled Flowfield around a Pitching Airfoil by DBD Plasma Actuator
Hiroaki FukumotoHikaru AonoMotofumi TanakaHisashi MatsudaToshiki OsakoTaku NonomuraAkira OyamaKozo Fujii
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Plasma actuator
To expand the airfoil database and realize the reverse digital airfoil design, this paper proposes a new sectional expression function of wind turbine airfoil based on the Joukowski transformation and derives the function equation for the novel airfoil. Compared with the existing airfoil function, the new airfoil function can adjust the parameter values to control the relative thickness, relative thickness position, relative camber, and relative camber position of the airfoil. Taking the common airfoil (NACA63-212) as an example, the existing airfoil is fitted according to the expected direction. The maximum fitting deviation is 1.22135×10-3, better than the four existing methods for airfoil shape fitting, which demonstrates well the practicability and accuracy of this method. It also shows that changing the parameter values can generate a new airfoil to enrich the airfoil database. Therefore, the proposed method broadens the ideas for airfoil design and method research.
Camber (aerodynamics)
Relative wind
Position (finance)
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Abstract This study investigates the active flow control on NACA0012 airfoil numerically by introducing dielectric barrier discharge (DBD) plasma actuators. The flow over the airfoil simulations were performed using ANSYS program for free-stream velocity 14.6 m/s with wide range of angle of attacks (from 0 to 20 degrees) on NACA0012 airfoil with applied voltage 16 kV across the electrodes. There are several plasma actuator models, which simulate the effect of the plasma actuator. This paper focuses on two numerical methods: Shyy model and Suzen model. They depend on calculating the induced body force of the plasma and import it in Navier Stokes equation as an external body force. Mesh independence study is performed on the airfoil and validate the results without plasma activation with the experimental results. Two actuators were added at positions 0.1 and 0.3 of the chord length to the airfoil and an investigation is performed on the lift CL and drag Cd coefficients of the airfoil without and with the activation of the plasma. Thereafter, a comparison between the numerical results of two different plasma simulation models that were applied.
Plasma actuator
Flow Control
Chord (peer-to-peer)
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Optimization of the airfoil shape and flow-control device is critical for optimal performance of fluid devices, such as wind turbines and aircraft. In this study, the combined effects of an airfoil and a dielectric-barrier-discharge plasma actuator (DBD-PA), utilized as the flow-control device, were evaluated through surface pressure measurements in a wind-tunnel experiment using three types of airfoils: Göttingen 387, SG6043, and the NASA Common Research Model (NASA-CRM). Our experimental results demonstrated that combining the DBD-PA with either the SG6043 or NASA-CRM foil improved the maximum lift of the airfoil; the DBD-PA with the Göttingen 387 foil maintained lift even after the stall angle. These results indicate that the flow-control performance of a DBD-PA varies not only with the Reynolds number but also with the shape of the airfoil.
Plasma actuator
Stall (fluid mechanics)
Flow Control
Ion wind
Lift (data mining)
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This paper presents a review of aerofoil shape parameterisation methods that can be used for aerodynamic shape optimisation. Six parameterisation methods are considered for a range in design variables: Class function/Shape function Transformations (CST); B-splines; Hicks-Henne bump functions; a domain element approach using Radial Basis functions (RBF); Bezier surfaces; and a singular value decomposition modal extraction method (SVD); plus the PARSEC method. The performance of each method is analysed by considering geometric shape recovery on over 1000 aerofoils using a range of design variables, testing the efficiency of design space coverage. A more in-depth analysis is then presented for three aerofoils, NACA4412, RAE2822 and ONERA M6 (D section), with geometric error and convergence of the resulting aerodynamic properties presented. In the large scale test it is shown that, for all the methods, a large number of design variables are needed to achieve significant design space coverage. For example at least 25 design variables are needed to cover 80% of the design space regardless of the method used; this is often higher than is desired for two-dimensional studies, suggesting that further work may be required to reduce the number of design variables needed.
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Aerodynamics as a branch of science is based on many idealized concepts and ingenious abstractions and approximations. The teaching of aerodynamics, in this context, becomes a challenging undertaking. In order to demonstrate the relevance of these concepts to real situations, it is important that appropriate experimental demonstrations are devised. In this paper we describe such an experimental programme to demonstrate the usefulness and limitations of thin airfoil theory in the analysis of the aerodynamic characteristics of an airfoil. This programme is easy to implement and has been incorporated in the teaching of aerodynamics to undergraduate students at the University of New South Wales.
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Optimization of airfoil shape using evolutionary algorithms is becoming a trend in design of blades for turbomachines and aircraft. Evolutionary algorithms work with parameterization of airfoil shape, i.e. representation of airfoil with the help of some parameters which control its shape. Thus, one of the challenges in this field is to describe the airfoil with suitable parameters and explicit or implicit mathematical functions. This paper discusses various parameterization techniques being used to parameterize the airfoil.
Representation
NACA airfoil
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This report deals with the effect of small variations in ordinates specified by different laboratories for the airfoil section. This study was made in connection with a more general investigation of the effect of small irregularities of the airfoil surface on the aerodynamic characteristics of an airfoil. These tests show that small changes in airfoil contours, resulting from variations in the specified ordinates, have a sufficiently large effect upon the airfoil characteristics to justify the taking of great care in the specification of ordinates for the construction of models.
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In low Reynolds numbers region's flow, a laminar separation region and separation bubble are observed on an airfoil surface, these separation flow contribute to become worse aerodynamic characteristics of the airfoil. We intended to improve the aerodynamics of a NACA0012 airfoil using a pulsed DBD plasma actuator as a flow control device for suppressing the separated flow. We visualized and measured the flow field around the NACA0012 airfoil to examine an effect of induced flow by the plasma actuator at 30,000 of Reynolds number. As the results, we confirmed that a suppressing of separation flow were changed by flow field existing vortices on the airfoil surface which depend on F+ changing.
Plasma actuator
Flow Control
Separation (statistics)
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Active flow control by plasma actuators is a topic of great interest by worldwide scientific community. These devices are mainly used for boundary layer control in order to improve the aerodynamic performance of aerial vehicles. Plasma actuators are simple devices that produces a wall bounded jet which allow to control the adjacent flow without moving mechanical parts. Recently, new geometries have been proposed by different authors in an attempt to improve the performance of these devices. In this work, some of these new configurations will be studied and compared considering its ability for boundary layer control applications. Dielectric Barrier Discharge (DBD) plasma actuator, Plasma Synthetic Jet (PSJ) actuator, Multiple Encapsulated Electrodes (MEE) plasma actuator and Curved plasma actuator (or 3D plasma actuator) will be experimentally studied in this work. Plasma actuators power consumption was measured by two different experimental methods. Results for power consumption and power losses of different plasma actuators geometries were presented and discussed.
Plasma actuator
Flow Control
Synthetic jet
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