Lift Enhancement by Plasma Actuators at Low Reynolds Numbers

Vorobiev, Alexander; Rennie, Mark R.; Jumper, Eric J.

doi:10.2514/6.2010-4836

Cited by 6 publications

(5 citation statements)

References 9 publications

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“…It was shown that the non-uniform spanwise forcing created by the plasma actuator suppressed the appearance of coherent two-dimensional modes to accelerate the transition process. Vorobiev, Rennie & Jumper (2013) conducted flow separation control of a NACA 0009 airfoil at the Reynolds numbers of 70 000-400 000, where laser Doppler velocimetry (LDV) measurements were performed to study the effect of a DBD plasma actuator. The results indicated that the effectiveness of plasma actuators in trailing-edge separation control depended on the state of the boundary layer at the actuator location.…”

Section: Plasma Flow Controlmentioning

confidence: 99%

Flow control over an airfoil using virtual Gurney flaps

2015

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Flow control over a NACA 0012 airfoil is carried out using a dielectric barrier discharge (DBD) plasma actuator at the Reynolds number of 20 000. Here, the plasma actuator is placed over the pressure (lower) side of the airfoil near the trailing edge, which produces a wall jet against the free stream. This reverse flow creates a quasi-steady recirculation region, reducing the velocity over the pressure side of the airfoil. On the other hand, the air over the suction (upper) side of the airfoil is drawn by the recirculation, increasing its velocity. Measured phase-averaged vorticity and velocity fields also indicate that the recirculation region created by the plasma actuator over the pressure surface modifies the near-wake dynamics. These flow modifications around the airfoil lead to an increase in the lift coefficient, which is similar to the effect of a mechanical Gurney flap. This configuration of DBD plasma actuators, which is investigated for the first time in this study, is therefore called a virtual Gurney flap. The purpose of this investigation is to understand the mechanism of lift enhancement by virtual Gurney flaps by carefully studying the global flow behaviour over the airfoil. First, the recirculation region draws the air from the suction surface around the trailing edge. The upper shear layer then interacts with the opposite-signed shear layer from the pressure surface, creating a stronger vortex shedding from the airfoil. Secondly, the recirculation region created by a DBD plasma actuator over the pressure surface displaces the positive shear layer away from the airfoil, thereby shifting the near-wake region downwards. The virtual Gurney flap also changes the dynamics of laminar separation bubbles and associated vortical structures by accelerating laminar-to-turbulent transition through the Kelvin-Helmholtz instability mechanism. In particular, the separation point and the start of transition are advanced. The reattachment point also moves upstream with plasma control, although it is slightly delayed at a large angle of attack.

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Section: Plasma Flow Controlmentioning

confidence: 99%

Flow control over an airfoil using virtual Gurney flaps

2015

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“…Solving this problem is challenging, and current works focus on making temporary lift. Some studies control a high lift device as a powered high-lift system [9] [10], and another has to employ plasma actuators [11]. These solutions, however, need extra devices to increase the weight and the response of these devices are not fast enough for safety improvement.…”

Section: B Objectivementioning

confidence: 99%

Lift control of electric airplanes by using propeller slipstream for safe landing

Konishi

Fujimoto

Watanabe

et al. 2015

2015 IEEE International Conference on Mechatronics (ICM)

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Aircrafts are desired to be more energy efficient and safer due to the increasing demand for air transportations. However, generally speaking, nowadays commercial airplanes tend to loss stability under wind disturbances, especially during landing. On the other hand, electric airplanes (EAs) are believed to satisfy the two demands because electric motors are used for the propulsion. Especially, as the actuators, electric motors can improve the control performances of EAs compared with internal combustion engines (ICEs). In this paper, by utilizing electric motors' advantages, lift control method using propeller slipstream is proposed for safe landing, which might be a key technology to innovate the design of EAs. Moreover, simulations and experiments are conducted to verify the effectiveness of the proposed method.

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“…Eta palen diseinurako erabakiak fluxu artifizial horietan lorturiko emaitzen arabera hartzeak ezustekoak ekar ditzake. Hala ere, metodologia hau praktika orokortua da, eta palen hobekuntza aerodinamikoa lortzeko moldaketa anitz gehitu izan dira, moldaketa horiek baldintza artifizialetan soilik testeatuz (Vorobiev et al, 2013;Van Treuren, 2015;Meng et al, 2018). Baina Van Treuren ikertzaileak (2015) laneko ondorioetan azaltzen duen moduan, beharrezkoa da baldintza errealak erreproduzitzen hastea diseinu prozedura egoki bat izateko.…”

Section: Arloko Egoera Eta Ikerketaren Helburuakunclassified

Industria eolikoko palen efizientzia aerodinamikoaren azterketa esperimentala baldintza ideal eta errealetan

Zarketa-Astigarraga¹,

Peñalba²,

Mayor³

et al. 2021

IV. Ikergazte. Nazioarteko Ikerketa Euskaraz. Kongresuko Artikulu Bilduma. Ingeniaritza Eta Arkitektura

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Energia berriztagarrien paradigmak erronka ugari dakartza berorrekin, epe laburrean erantzun beharrekoak bederen. Energia eolikoaren kasuan, ustiapena ohiko haize-parkeetatik itsasalde edota hiriguneetara mugitzean datza, inpaktu bisuala nahiz ingurumen kalteak murrizteko asmoz. Horrek haizearen fluxu baldintzak nabarmen aldatzea dakar; bereziki, turbulentzia eta ingurumen-eragileek sorturiko gainazal-zimurtasuna hartu behar da kontuan eta, hiriguneetako kasuan, aerosorgailuen eskala aldaketa. Haize-tunel bidezko entseguak burutuz, faktore horiek NACA0021 geometriadun pala baten efizientzia aerodinamikoan duten eragina aztertu da, baldintza idealetatik errealetara igarotzean ematen den efizientzia galera ikusaraziz. Galera hori dela-eta, entsegu esperimentalak harik eta baldintza errealenetan egiteko beharra ondorioztatzen da.

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Lift Enhancement by Plasma Actuators at Low Reynolds Numbers

Cited by 6 publications

References 9 publications

Flow control over an airfoil using virtual Gurney flaps

Flow control over an airfoil using virtual Gurney flaps

Lift control of electric airplanes by using propeller slipstream for safe landing

Industria eolikoko palen efizientzia aerodinamikoaren azterketa esperimentala baldintza ideal eta errealetan

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