Flow past a square prism with an upstream control rod at incidence to uniform stream

Fırat, Erhan; Akansu, Yahya Erkan; Akıllı, Hüseyin

doi:10.1016/j.oceaneng.2015.08.041

Cited by 25 publications

(15 citation statements)

References 39 publications

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“…Smoke-wire flow visualization experiment is performed to see the flow field around a symmetrical airfoil NACA 0012 and a circular cylinder at Re C = 3.610 4 . Figure 3 shows flow phenomena such as flow separation, attachment and reattachments on the bodies.…”

Section: Flow Visualizationmentioning

confidence: 99%

“…As seen in Figure 13, variation of the drag coefficients of the cylinder as a function of S/D is plotted at the Reynolds number of 2.510 4 . Drag coefficient is obtained from mean pressure measurement data.…”

Section: Drag Coefficientsmentioning

confidence: 99%

“…Flow control around the cylinder with the help of control rod [1][2][3][4], splitter plate [5][6][7] can be given as literature examples. Especially, flow around a circular cylinder has encountered in many engineering applications, for example, in the cooling tower, chimney and so forth.…”

Section: Introductionmentioning

confidence: 99%

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Bi̇r Kanat Profi̇li̇ Ve Bi̇r Dai̇resel Si̇li̇ndi̇r Etrafindaki̇ Akişin Aerodi̇nami̇k Karakteri̇skti̇kleri̇

Sarıoğlu

2017

Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi

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The flow characteristics around a symmetrical airfoil NACA 0012 at incidence and a circular cylinder placed in tandem have been studied experimentally at a Reynolds number of 1.510 5 based on the chord length of the airfoil C. The downstream circular cylinder of diameter D = 25 mm used as a bluff body was placed in the same axis in the flow direction in the wake of the airfoil. The dimensionless gap S/D, where S is the longitudinal spacing between the airfoil and the cylinder, and the attack angle of the airfoil, , were varied from 0 to 4.3 and from 0° to 15°, respectively. The effects of the attack angle of the airfoil and the longitudinal spacing between the airfoil and the cylinder on the pressure distributions and vortex shedding were examined. Characteristics of the vortex formation region and locations of flow attachments, reattachments, and separations were observed by means of the flow visualizations. It has been seen that the airfoil and the cylinder have considerably affected by each other. The variation in the flow structures according to the attack angle of the airfoil and the longitudinal spacing between the airfoil and the cylinder are revealed utilizing the flow visualization photographs.Keywords: Airfoil, circular cylinder, aerodynamic characteristic, pressure distribution, Strouhal number BİR KANAT PROFİLİ VE BİR DAİRESEL SİLİNDİR ETRAFINDAKİ AKIŞIN AERODİNAMİK KARAKTERİSKTİKLERİ ÖZArdışık olarak yerleştirilmiş simetrik bir NACA 0012 kanat profili ve bir dairesel silindir etrafındaki akış karakteristikleri kiriş uzunluğuna göre tanımlanmış Reynolds sayısının 1,510 5 değerinde deneysel olarak incelenmiştir. Bir küt cisim olarak kullanılan 25 mm çapındaki dairesel silindir, kanat profilinin iz bölgesinde akış yönünde aynı eksende yerleştirilmiştir. Boyutsuz boşluk S/D (burada S, kanat profili ile silindir arasındaki uzunlamasına boşluktur) ve kanat profili hücum açısı, , sırasıyla 0'dan 4,3'e ve 0°'den 15°'ye kadar değiştirilmiştir. Kanat profili hücum açısının ve kanat profili ile silindir arasındaki uzunlamasına boşluğun basınç dağılımı ve girdap kopması üzerine etkileri incelenmiştir. Girdap oluşum bölgesi ve akış tutunması, tekrar tutunması ve ayrılma konumları, akış görüntüleme yardımıyla gözlenmiştir. Kanat profili ve dairesel silindirin önemli derecede birbirlerini etkiledikleri görülmüştür. Kanat profili hücum açısı ve uzunlamasına boşluk mesafesine göre akış yapılarındaki değişim, akış gözlem fotoğrafları kullanılarak açıklanmıştır.Anahtar Kelimeler: Kanat profili, dairesel silindir, aerodinamik karakteristik, basınç dağılımı, Strouhal sayısı * Corresponding author / Sorumlu yazar.

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Section: Flow Visualizationmentioning

confidence: 99%

Section: Drag Coefficientsmentioning

confidence: 99%

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Bi̇r Kanat Profi̇li̇ Ve Bi̇r Dai̇resel Si̇li̇ndi̇r Etrafindaki̇ Akişin Aerodi̇nami̇k Karakteri̇skti̇kleri̇

Sarıoğlu

2017

Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi

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“…These forces are generally undesired. To decrease them on the body, shear layers must be controlled before (boundary layer) and/or after (free shear layers) the separation [1][2][3][4][5][6][7][8][9][10]. The aim of this study is firstly to alter the near-wake structure of the cylinder using guiding plates, and then, to interpret the foregoing physics of the near-wake in terms of patterns of time-averaged vorticity and streamlines, timeaveraged and fluctuating velocity components, and spectral analysis; secondly to predict the trend of timeaveraged drag coefficient and root-mean-square of the fluctuating lift coefficient numerically in the absence of the direct force measurements.…”

Section: Introductionmentioning

confidence: 99%

An investigation of the near-wake flow structure of a cylinder with guiding plates

Ekinci¹,

Fırat²,

Ozkan³

et al. 2018

EPJ Web Conf.

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In this study, the flow behind a circular cylinder with a pair of outer identical guiding plates was investigated using particle image velocimetry (PIV) for various angular positions of the plates (i.e. α=±70°, ±100°, and ±130°). The gaps between these plates and cylinder are equal and are 0.3D. Experiments were carried out at a subcritical Reynolds (Re=ρ·U∞·D/μ) number of 7500, based on the cylinder diameter (D) and the flow velocity (U∞). The features of the near-wake with and without the guiding plates were interpreted in terms of patterns of time-averaged vorticity and streamlines, time-averaged and fluctuating velocity components. The spectral analysis was also carried out to determine the time-dependent variation of the transverse velocity at given locations in the near-wake. Two-dimensional computations of flow around circular cylinders with and without guiding plates have also been performed to predict the timeaveraged and root-mean-square of force coefficients of the various models. It was seen that the guiding plates at an appropriate angular position can lead to substantial attenuation, or retardation, of the process of large-scale vortex formation in the near-wake, thus can lead to vortex-induced vibration (VIV) suppression without any increase in drag.

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“…A moving surface (Zhang et al 2010), a dielectric barrier discharge actuator (Akansu et al 2013;Akbıyık et al 2016), suction and blowing (Li et al 2003), a vortex generator (Volino and Ibrahim 2012) and a piston cylinder mechanism (Gilarranz et al 2005) can be given as examples of AFC methods. Splitter plates (Akansu et al 2004;Sarioglu et al 2006), passive vortex generators (Godard and Stanislas 2006) control rod (Akansu et al 2011;Fırat et al 2015;Sarioglu et al 2005) and dimples (Bearman and Harvey 1993) can be listed as examples of PFC methods. Sarioglu et al (2006) studied the influence of adding a plate to a square prism with ratio L/D=1.…”

Section: Introductionmentioning

confidence: 99%

Ayirici Plakali Bi̇r Kare Pri̇zma Etrafindaki̇ Akişta Hücum Açisinin Etki̇si̇

Seyhan¹,

Sarıoğlu²,

Akansu³

2018

Uludağ University Journal of the Faculty of Engineering

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Lift and drag forces on a square prism with a (splitter) plate are experimentally investigated by force measurements with a load cell. Results showed that drag and lift coefficients are independent of Reynolds number for Re = 9700-36500 at 0°, 45°, 90°, 135° and 180°. Drag coefficient at 0 is obtained as 2.02 for the square prism alone, and 1.04 for the square cylinder with splitter plate. Maximum drag reduction for the square cylinder with the plate is 50% as compared to the square cylinder at 0 and 15. For α < 30° and α > 114°, drag coefficient of a square prism with splitter plate is smaller than that of the square prism alone. At Re = 20000, lift and drag coefficients significantly change with increasing attack angle.

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Flow past a square prism with an upstream control rod at incidence to uniform stream

Cited by 25 publications

References 39 publications

Bi̇r Kanat Profi̇li̇ Ve Bi̇r Dai̇resel Si̇li̇ndi̇r Etrafindaki̇ Akişin Aerodi̇nami̇k Karakteri̇skti̇kleri̇

Bi̇r Kanat Profi̇li̇ Ve Bi̇r Dai̇resel Si̇li̇ndi̇r Etrafindaki̇ Akişin Aerodi̇nami̇k Karakteri̇skti̇kleri̇

An investigation of the near-wake flow structure of a cylinder with guiding plates

Ayirici Plakali Bi̇r Kare Pri̇zma Etrafindaki̇ Akişta Hücum Açisinin Etki̇si̇

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