Design and Characterization of an Experimental Setup for Active Control of Dynamic Stall over a NACA 0012 Airfoil

Castaneda, David; Whiting, Nicole; Webb, Nathan J.; Samimy, Mo

doi:10.2514/6.2019-3212

Cited by 4 publications

(8 citation statements)

References 25 publications

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“…[23] DBD Plazma Deneysel 3,35  10 5 Castaneda vd. [24] NS-DBD Plazma Deneysel 5,00  10 5 Durasiewicz vd. [25] NS-DBD Plazma Sayısal 7,40  10 5 Duvigneau vd.…”

Section: Geometrik Parametreler (Geometrical Parameters)unclassified

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Computational fluid dynamics study of lift enhancement on a NACA0012 airfoil using a synthetic jet actuator

ÇANLIOĞLU¹,

Kara

2023

Gazi Üniversitesi Mühendislik Mimarlık Fakültesi Dergisi

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Bu çalışmada, hoparlör tipi sentetik jet eyleyici (SJE) kullanarak iki boyutlu sayısal analizler yapılmıştır. Kanat profilinin aerodinamik özelliklerini geliştirmek için SJE'nin hangi frekans ve jet orifis çapında olması gerektiğinin bulunması amaçlanmıştır. Hesaplamalı akışkanlar dinamiği (HAD) metodu, ANSYS Fluent akış çözücü modülünde, SST k-ω türbülans modeliyle Reynolds ortalamalı Navier-Stokes (RANS) ve daimi olmayan RANS (URANS) denklemlerinde göre kullanılmıştır. Ağ yakınsama indeksi testi HAD analizlerinde ve SJE-kapalı konfigürasyon çalışmasının HAD analizlerinde RANS, diğer tüm analizlerde URANS çözümleri yapılmıştır. Ağ yakınsama indeksi testi sonucunda, düğüm sayısının 34700 olduğu Mesh4 isimli ağ yapısı hem kaldırma hem de direnç katsayısı hesabına göre en uygun ağ yapısı olarak seçilmiştir. Seçilen referans çalışmalara göre farklı açı ve Reynolds sayılarında, 1500’den 2200 Hz’e frekans ve 1 mm’den 3 mm’ye orifis çapı değerlerinde HAD analizleri yapılmış, kaldırma katsayısı SJE-kapalı ve SJE-açık durumlarında kanat profili üzerinde incelenmiştir. Son olarak, SJE tarafından CL ve kaldırma-direnç oranı (CL/CD) iyileştirmesi farklı konfigürasyonlar altında karşılaştırılmıştır. Sonuçlara göre bu katsayılar, düşük ve orta değerlerdeki Reynolds sayılarında etkili bir şekilde artmıştır.

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“…[23] DBD Plazma Deneysel 3,35  10 5 Castaneda vd. [24] NS-DBD Plazma Deneysel 5,00  10 5 Durasiewicz vd. [25] NS-DBD Plazma Sayısal 7,40  10 5 Duvigneau vd.…”

Section: Geometrik Parametreler (Geometrical Parameters)unclassified

“…Castaneda vd. [24] NACA0012 kanat profili üzerinde dinamik tutunma kaybı kontrolü için nanosaniyelik darbe ile sürülen DBD tipi (NS-DBD) eyleyici kullanımını Re=3×10 5 ile Re=5×10 5 aralığında deneysel olarak göstermişlerdir. Bu çalışmada nanosaniyelik yerel ısıl çarpılma kullanımıyla, Vaddi vd.…”

Section: Giriş (Introduction)unclassified

Computational fluid dynamics study of lift enhancement on a NACA0012 airfoil using a synthetic jet actuator

ÇANLIOĞLU¹,

Kara

2023

Gazi Üniversitesi Mühendislik Mimarlık Fakültesi Dergisi

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“…The modifications can also become a source of noise and vibration so it is difficult to make a big breakthrough via passive flow control techniques. 5 These potential disadvantages motivate research into active flow control.…”

Section: Introductionmentioning

confidence: 99%

“…13 At present, dynamic stall controlled by NS-DBD actuation has become a research hotspot while the research achievements are few. Starikovskiy and colleagues 14–17 from Princeton University and Samimy and colleagues 5,18–20 from Ohio State University pioneer the research in this area. Starikovskiy et al 14 have confirmed that NS-DBD can alleviate the dynamic stall for a Reynolds number of 4.5 × 10 5 and reduced frequency of 0.02.…”

Section: Introductionmentioning

confidence: 99%

“…Samimy and colleagues 18 have carried out experimental research at combinations of different Reynolds numbers ( Re = 1.67 × 10 5 , 3 × 10 5 , 5 × 10 5 ), different reduced frequencies ( k = 0.025–0.075), and different actuation frequencies ( St e = 0–10), 19 and find that NS-DBD results in earlier reattachment and preliminary reveal the control mechanism of different actuation frequencies. 5,20 However, these studies are far from enough.…”

Section: Introductionmentioning

confidence: 99%

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Nanosecond dielectric barrier discharge–based dynamic stall control on an SC-1095 airfoil

Yang

Liang

Zhao

2020

Proceedings of the Institution of Mechanical Engineers, Part I:

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Dynamic stall is a time-dependent flow separation and stall phenomenon that is present in many applications, including violently maneuvering aircraft, surging compressor, wind turbine, and, most observably, rotorcraft. Nanosecond dielectric barrier discharge plasma actuator has previously demonstrated the control ability in static stall conditions and shows promise to address dynamic stall. The present work explores the ability of nanosecond dielectric barrier discharge to control dynamic stall over an SC-1095 airfoil and summarizes the control law of actuation parameters. The actuation voltage, actuation frequency, and reduced frequencies were varied over large ranges: Vp–p = 7–13 kV, F+ = 0.5–10, and k = 0.05–0.15. Direct aerodynamic measurements were taken for each combination of actuation voltages and actuation frequencies, and fixed combination at different experimental reduced frequencies. It was observed that nanosecond dielectric barrier discharge could effectively improve the dynamic stall characteristics, and three major conclusions were drawn. First, there is a threshold for actuation voltage. Only when the actuation voltage is greater than or equal to the threshold voltage can the separation be effectively suppressed and the steep stall can be alleviated. Second, High F+ has better control performance of maintaining peak lift in the stall regime and achieves better effects in moment control and drag reduction while lift reattachment is better with low F+ on downstroke. Last, with the increase of reduced frequency, the control effect of nanosecond dielectric barrier discharge with settled actuation parameter combination becomes worse, so greater cost needs to be paid for effective control at a larger reduced frequency.

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Effect of blade thickness on rotating stall of mixed-flow pump using entropy generation analysis

Shi

et al. 2021

Energy

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Design and Characterization of an Experimental Setup for Active Control of Dynamic Stall over a NACA 0012 Airfoil

Cited by 4 publications

References 25 publications

Computational fluid dynamics study of lift enhancement on a NACA0012 airfoil using a synthetic jet actuator

Computational fluid dynamics study of lift enhancement on a NACA0012 airfoil using a synthetic jet actuator

Nanosecond dielectric barrier discharge–based dynamic stall control on an SC-1095 airfoil

Effect of blade thickness on rotating stall of mixed-flow pump using entropy generation analysis

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