Flow characteristics and tip vortex formation around a NACA 0018 foil with anendplate

Gim, Ok-Sok; Lee, Gyoung-Woo

doi:10.1016/j.oceaneng.2012.12.009

Cited by 24 publications

(11 citation statements)

References 16 publications

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“…Se calibró utilizando un Furness Controls FCO510 (Eboibi, Danao, y Howell, 2016). Fuente: (Gim & Lee, 2013) El sistema PIV consta de un optical láser LED y una cámara digital de alta velocidad FASTCAM-X 1280PCI. La cámara digital de la figura 19; provee una resolución de 1280 x1024 pixeles y velocidad de 500 fps (imágenes por segundo) (Gim & Lee, 2013).…”

Section: Figura 16 Calibrador De Hilos Calientesunclassified

“…Fuente: (Gim & Lee, 2013) Metodología Se empleó la revisión bibliográfica (documental) que se compone de las siguientes fases: definir los objetivos que se trata de establecer parámetros de alcanza para el desarrollo de la investigación, se seleccionó la literatura acorde al tema de investigación de bases de datos como: Scielo, Dialnet, Scopux y Elservier, para ello se empleó mapas mentales para encaminar lógica en el desarrollo. Delimitado la literatura de los 7 años anteriores que arrojo lo siguiente: artículos publicados en el año 2013(2), 2016(6), y 2018(6), los mismos que perteneces a estudios a nivel mundial.…”

Section: Figura 19 Cámara De Alta Velocidadunclassified

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Instrumentación empleada en túneles de viento subsónicos para evaluar perfiles aerodinámicos

Chuquitarco¹,

Carrera²,

Osorio³

et al. 2019

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Los túneles de viento son equipos indispensables en el desarrollo de experimentos aerodinámicos donde se requieren obtener condiciones de borde controladas para garantizar la repetitividad en cada ensayo. Los datos obtenidos en las pruebas realizadas en túneles de viento deben ser extraídos de manera efectiva para que sean interpretados por el analista, por tal motivo existen variedad de instrumentos especializados con los cuales se logra una alta sensibilidad en las mediciones y permiten extraer información indispensable ya sea para el desarrollo de nuevos productos y equipos o mejorar el entendimiento de fenómenos naturales. El objetivo se direccionó a identificar los diferentes tipos de instrumentación empleados para la recolección de datos en túneles de viento subsónicos. El método aplicado para la elaboración de este artículo fue la revisión bibliográfica de varios autores, el mismo que se compone de varias etapas como: definición de los objetivos, selección de bibliografía, análisis de la literatura y redacción. Posterior a la revisión bibliográfica se identificó que existen variedad de instrumentos de medición. Entre los cuales los más comúnmente empleados son: transductores de fuerza para determinar fuerzas de sustentación, arrastre y momento, sensores para la toma de presión estática, tomas de presión total, sondas de velocidad de hilo caliente y sondas de cinco agujeros. Por tal motivo, este artículo tendrá como propósito establecer referencias para conocer los diferentes tipos de instrumentación y sus aplicaciones primordiales en el proceso de extracción de datos al analizar elementos en un túnel de viento.

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Section: Figura 16 Calibrador De Hilos Calientesunclassified

Section: Figura 19 Cámara De Alta Velocidadunclassified

Instrumentación empleada en túneles de viento subsónicos para evaluar perfiles aerodinámicos

Chuquitarco¹,

Carrera²,

Osorio³

et al. 2019

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show abstract

“…Based on the conducted experimental works in this field, one may conclude that they can provide evidence about the generated tip vortices, the induced drag, show us the possibility of the occurrence of the cavitation, and finally present to us the essential effects of adding different flow controlling items such as endplate (Gim & Lee 2013) or flaps (Sterenborg et al 2014), to the air/hydrofoil. However, the main problem is the difficulty of such a study, which needs accurate experimental equipment involved in wind or cavitation tunnels, which may also result in high costs (Mahon & Zhang 2005).…”

Section: Introductionmentioning

confidence: 98%

RANS simulation of the tip vortex flow generated around a NACA 0015 hydrofoil and examination of its hydrodynamic characteristics

Ghadimi

Tanha

Tavakoli

et al. 2017

Journal of Marine Engineering & Technology

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Understanding the flow behaviour of the tip vortex around hydrofoils, the corresponding pressure distribution and generated tip vortices are the key factors for prediction of cavitation inception and acoustic noise generation. Accordingly, numerical simulation of tip vortex flow generated around a National Advisory Committee for Aeronautics' hydrofoil (NACA 0015) is hereby investigated in the present study. To this end, the commercial software Ansys-CFX is applied, and Navier-Stokes equations are solved. Numerical simulations are performed using k-ω Shear Stress Transport (SST) model turbulence model. Validity of the solution is examined by comparing the obtained results against available experimental data for pressure coefficient distribution and lift coefficient (CL). Moreover, the lift and drag coefficients are computed and presented at different angles of attack. The velocity vector fields along with generated tip vortices are also presented. Two different vortices are observed, which are combined in the neighbourhood of trailing edge. On the other hand, the pressure distribution at the tip section is reported and effects of tip vortex on pressure variations are displayed and analysed. Ultimately, the streamlines are illustrated, and flow behaviour in the tip area and at the wake of the NACA hydrofoil is investigated.

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“…In this range of Reynolds number, the trend of flow in suction surface of the airfoil is to be separated. On the other hands, the reverse pressure gradient that occurs in low Reynolds number airfoils causes the flow separation [8]. As the angle of attack increases, the vertical velocity and, consequently, the lift coefficient are escalated.…”

Section: Introductionmentioning

confidence: 99%

A Numerical Investigation of Co-flow Jet Effects on Airfoil Aerodynamic Characteristics

Yazdani

Salimipour

2021

Preprint

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The present paper numerically investigates the performance of a Co-Flow Jet (CFJ) on the static and dynamic stall control of the NACA 0024 airfoil at Reynolds number 1.5 × 105. The two-dimensional Reynolds-averaged Navier-Stokes equations are solved using the SST k-ω turbulence model. The results show that the lift coefficients at the low angles of attack (up to α = 15̊) are significantly increased at Cµ = 0.06, however for the higher momentum coefficients, it is not seen an improvement in the aerodynamic characteristics. Also, the dynamic stall for a range of α between 0̊ and 20̊ at the mentioned Reynolds number and with the reduced frequency of 0.15 for two CFJ cases with Cµ = 0.05 and 0.07 are investigated. For the case with Cµ = 0.07, the lift coefficient curve did not present a noticeable stall feature compared to Cµ = 0.05. The effect of this active flow control by increasing the Reynolds numbers from 0.5 × 105 to 3 × 105 is also investigated. At all studied Reynolds numbers, the lift coefficient enhances as the momentum coefficient increases where its best performance is obtained at the angle of attack α = 15̊.

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Flow characteristics and tip vortex formation around a NACA 0018 foil with anendplate

Cited by 24 publications

References 16 publications

Instrumentación empleada en túneles de viento subsónicos para evaluar perfiles aerodinámicos

Instrumentación empleada en túneles de viento subsónicos para evaluar perfiles aerodinámicos

RANS simulation of the tip vortex flow generated around a NACA 0015 hydrofoil and examination of its hydrodynamic characteristics

A Numerical Investigation of Co-flow Jet Effects on Airfoil Aerodynamic Characteristics

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