Computational study into the flow field developed around a cascade of NACA 0012 airfoils

Ahmed, Noor A.; Yilbaş, Bekir Sami; Budair, M. O.

doi:10.1016/s0045-7825(98)00104-2

Cited by 11 publications

(8 citation statements)

References 11 publications

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“…There are various kinds of airfoils that have been developed for low Reynolds number operation. One of such airfoils is NACA 0012 which has been extensively investigated and reliably used for various applications at low Reynolds numbers [37,[50][51][52][53][54]. We selected this airfoil primarily because it is symmetrical and thus it will be relatively easier to manufacture the blades.…”

Section: Airfoil Selectionmentioning

confidence: 99%

“…The average flow Reynolds number of the turbine, as defined by equation (1.42), calculated at mid-radius under the design point operating condition (wind speed=4.0 m/s and tip-speed ratio=4.1) was found to be around 40,000. NACA 0012 airfoil template was selected for the blade design, which is a suitable airfoil for low Reynolds number applications [37,[50][51][52][53][54]. In addition, it is symmetrical along the camber line and thus it provides simplicity from construction point of view and minimizes the chances of manufacturing related defects.…”

Section: Design Specificationsmentioning

confidence: 99%

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Small-scale wind energy portable turbine (SWEPT)

Kishore

Coudron

Priya

2013

Journal of Wind Engineering and Industrial Aerodynamics

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ABSTRACTguidance, support and encouragement. He has been a great mentor and I have learned a lot from him, both in academic research and in personal life. He didn't only provide me the necessary infrastructure and resources to complete this project, but also gave me enough freedom and opportunities to test and implement my own ideas. He always encouraged me to think 'out of box' and allowed me to work on several other projects apart from the subject of this thesis. Prof. Priya has his own style; his dedication towards the work, his courage and conviction to take new challenges, his optimism, and the most importantly, his attachment with the students are few of the many qualities that has always inspired me and will always motivate me in future to move ahead.I would also like to extend my heartfelt gratitude to Prof. Walter O'Brien and Prof.Danesh Tafti for mentoring me in many academic courses and serving on my MS committee.

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Section: Airfoil Selectionmentioning

confidence: 99%

Section: Design Specificationsmentioning

confidence: 99%

Small-scale wind energy portable turbine (SWEPT)

Kishore

Coudron

Priya

2013

Journal of Wind Engineering and Industrial Aerodynamics

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“…The characteristics of flow inside channels are strongly related to the wall effects and the Reynolds number. They predicted accurately the trailing edge separation at different angles of attack for solidity ratios and staggers, showing that solidity increases the incidence at which maximum lift is obtained and Ahmed et al [9] modelled the steady flow in a linear cascade of NACA 0012 airfoils also using the k−ε turbulence model. Kim et al [1] performed a fully spectral direct numerical simulation (DNS) analysis for three-dimensional (3D) incompressible turbulent channel flow at low Reynolds number (Re) of 3300 (based on the centralline velocity) and the friction Reynolds number, Re τ = 180, with a 192 × 129 × 160 grid in the x, y, z directions.…”

Section: Introductionmentioning

confidence: 96%

“…Yilbas et al [8] simulated the flow field around a cascade of NACA 0012 airfoils employing the κ−ε model turbulence model. They predicted accurately the trailing edge separation at different angles of attack for solidity ratios and staggers, showing that solidity increases the incidence at which maximum lift is obtained and Ahmed et al [9] modelled the steady flow in a linear cascade of NACA 0012 airfoils also using the k−ε turbulence model. They further investigated the BL development at the suction and the pressure surfaces of the airfoil, predicting the separation point at the airfoil surface at high angles of attack.…”

Section: Introductionmentioning

confidence: 96%

Numerical investigations of wall-bounded turbulence

Daud

Bég

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part C:

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This article investigates numerically the effects on turbulence in two important flow regimes -fully developed channel flow and flow past a NACA 0012 airfoil, using the commercial software -FLUENT 6.3. The solution accuracy is explored via a sensitivity study of mesh type and quality effects, employing different element types (e.g. quadrilateral and triangular). The significance of this article is to elucidate the effects of enhancement wall treatment and standard wall function on the turbulent boundary layer. Furthermore, three different turbulence models have been utilized in this study (k−ε, re-normalization group (RNG), and shear stress transport (SST) k−ω). The numerical solutions have been compared with available direct numerical simulation (DNS) and experimental data and very good correlation has been achieved. In addition, the statistical turbulence results related to the RNG turbulence model are shown to yield much closer correlation with DNS and experimental data. The effect of Reynolds number (Re τ = 590 and Re τ = 2320) is studied for the channel flow regime. The near wall resolution is examined in detail by controlling in the y + value. A particularly important objective in this study is to highlight the importance of validation in computational fluid dynamics (CFD) turbulence simulations and sustaining a high degree of accuracy, aspects which are often grossly neglected with industrial CFD software. The authors therefore hope to provide some guidance to applied aerodynamicists utilizing CFD in future studies.

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“…The central theme behind all these flow control techniques is to prevent or delay flow separation. This is achieved either by incorporating shape changes to the body (Shmilovich and Yadlin, 2009, 2008), moving the surface of the body (Modi, 1997; Ahmed et al , 1998; Patnaik and Wei, 2002), momentum injection (Patnaik and Wei, 2002), using synthetic jets (You and Moin, 2008), plasma actuators (Little et al , 2009), suction and blowing (Huang et al , 2004a), etc.…”

Section: Introductionmentioning

confidence: 99%

CFD simulation of momentum injection control past a streamlined body

Sahu

Patnaik

2011

International Journal of Numerical Methods for Heat &Amp; Fluid Flow

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PurposeThe purpose of this paper is to achieve high‐performance aerofoils that enable delayed stall conditions and achieve high lift to drag ratios.Design/methodology/approachThe unsteady Reynolds averaged Navier‐Stokes equations are employed in conjunction with a shear stress transport (κ‐ω) turbulence model. A control equation is designed and implemented to determine the temporal response of the actuator. A rotating element, in the form of an actuator disc, is embedded on the leading edge of NACA 0012 aerofoil, to inject momentum into the wake region. The actuator disc is rotated at different angular speeds, for angles of attack (α) between 00 and 240.FindingsPhenomena such as flow separation, wake vortices, delayed stall, wake control, etc. are numerically investigated by means of streamlines, streaklines, isobars, etc. Streamwise and cross‐stream forces on the aerofoil are obtained. The influence of momentum injection parameter (ξ) on the fluid flow patterns, and hence on the forces acting on the streamlined body are determined. A synchronization‐based coupling scheme is designed and implemented to achieve annihilation of wake vortices. A delayed stall angle resulted with an attendant increase in maximum lift coefficient. Due to delay and/or prevention of separation, drag coefficient is also reduced considerably, resulting in a high‐performance lifting surface.Research limitations/implicationsThe practicality of momentum injection principle requires both wide ranging and intensive further studies to move forward beyond the proof of concept stage.Practical implicationsDetermination of forces and moments on an aerofoil is of vital interest in aero‐dynamic design. Perhaps, runways of the future can be shorter and/or more pay load can be carried by an aircraft, for the same stall speed.Originality/valueThe paper describes how a synchronization‐based coupling scheme is designed and implemented along with the RANS solver. Furthermore, it is tested to verify the dynamic adaptability of the wake vortex annihilation for NACA 0012 aerofoils.

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Computational study into the flow field developed around a cascade of NACA 0012 airfoils

Cited by 11 publications

References 11 publications

Small-scale wind energy portable turbine (SWEPT)

Small-scale wind energy portable turbine (SWEPT)

Numerical investigations of wall-bounded turbulence

CFD simulation of momentum injection control past a streamlined body

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