An experimental study on aerodynamic sound generated from wake interference of circular cylinder and airfoil vane in tandem

Munekata, Mizue; Kawahara, Kaoru; Udo, Takamasa; Yoshikawa, Hiroyuki; Ohba, Hideki

doi:10.1007/s11630-006-0342-x

Cited by 13 publications

(24 citation statements)

References 8 publications

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“…In this range, the periodic Karman's vortex is generated from the circular cylinder. It was confirmed by the Strouhal number St in the flow visualization, which corresponds with that in the acoustic measurement, in our previous study [7] .…”

Section: Flow Visualizationsupporting

confidence: 83%

“…5 and U = 30 m/s. This interval condition of L/d = 10.5 is that of generating maximum sound pressure level at zero attack angle, by feedback system for fluid resonant oscillation, in our previous results [7] . The surface pressure is measured at 5 degrees intervals around the circular cylinder.…”

Section: Pressure Measurement Of Circular Cylinder Surfacementioning

confidence: 73%

“…The O.A.SPL, the peak SPL and the peak frequency decrease with increasing of α. It has been found that the DFN at α = 0° is caused by Karman's vortex generated from the upstream circular cylinder [7] . 5 is the highest in all interval data.…”

Section: Exploration Test Of Sound Sourcementioning

confidence: 99%

“…In our previous study [7] , the effects of the interval between the cylinder and the airfoil without attack angle on the characteristics of aerodynamic sound were investigated and compared with the cases of single body. It was presented that the downstream airfoil works as the sound source of DFN (Discrete Frequency Noise), which has the frequency of vortex shedding from the cylinder, when the interval of two bodies is longer than a critical distance.…”

Section: Introductionmentioning

confidence: 99%

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An experimental study on aerodynamic sound generated from wake interaction of circular cylinder and airfoil with attack angle in tandem

Munekata¹,

Koshiishi²,

Yoshikawa³

et al. 2008

J. Therm. Sci.

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In our previous study, the effects of the interval between the cylinder and the airfoil on the aerodynamic sound were investigated and compared with the cases of single circular and single airfoil. In this study, the effects of the attack angle of the airfoil located downstream on the characteristics of aerodynamic sound and the wake structure are investigated at a given interval between the cylinder and the airfoil. It is found that the sound pressure level of DFN and the peak frequency decrease with increasing attack angle of airfoil because of the diffusive wake structure due to the increased back pressure of circular cylinder, which is caused by the blocking effect of airfoil. It is shown that the sound sources are corresponded to the attack points of shedding vortex form the upstream circular cylinder to the downstream airfoil. We conclude that the pressure fluctuation at the airfoil surface effects on the sound pressure level, from the flow visualizations and the exploration test of sound source.

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Section: Flow Visualizationsupporting

confidence: 83%

Section: Pressure Measurement Of Circular Cylinder Surfacementioning

confidence: 73%

Section: Exploration Test Of Sound Sourcementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

An experimental study on aerodynamic sound generated from wake interaction of circular cylinder and airfoil with attack angle in tandem

Munekata¹,

Koshiishi²,

Yoshikawa³

et al. 2008

J. Therm. Sci.

Self Cite

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“…Munekata et al [24] investigated the aeroacoustic characteristic such as sound generated from interaction of airfoil and circular cylinder arranged in tandem. Flow visualization and acoustic measurements are carried out for the airfoil placed behind circular cylinder.…”

Section: Introductionmentioning

confidence: 99%

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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Wake-triggered secondary vortices over a cylinder/airfoil configuration

Wang

2022

Exp Fluids

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An experimental study on aerodynamic sound generated from wake interference of circular cylinder and airfoil vane in tandem

Cited by 13 publications

References 8 publications

An experimental study on aerodynamic sound generated from wake interaction of circular cylinder and airfoil with attack angle in tandem

An experimental study on aerodynamic sound generated from wake interaction of circular cylinder and airfoil with attack angle in tandem

Bi̇r Kanat Profi̇li̇ Ve Bi̇r Dai̇resel Si̇li̇ndi̇r Etrafindaki̇ Akişin Aerodi̇nami̇k Karakteri̇skti̇kleri̇

Wake-triggered secondary vortices over a cylinder/airfoil configuration

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