Experimental Study of Effects of Frequency for Burst Wave on a DBD Plasma Actuator for Separation

2016 ◽  
Author(s):  
Satoshi Sekimoto ◽  
Taku Nonomura ◽  
Kozo Fujii
Keyword(s):  
Experimental Study ◽  
Plasma Actuator ◽  
Dbd Plasma

scholarly journals Experimental Study on Anti-Icing Performance of NS-DBD Plasma Actuator

2018 ◽  
Vol 8 (10) ◽  
pp. 1889 ◽  
Author(s):  
Jie Chen ◽  
Hua Liang ◽  
Yun Wu ◽  
Biao Wei ◽  
Guangyin Zhao ◽  
...  
Keyword(s):  
Experimental Study ◽  
Heat Dissipation ◽  
Ccd Camera ◽  
Liquid Water Content ◽  
Pulse Frequency ◽  
Plasma Actuator ◽  
Voltage Amplitude ◽  
Dbd Plasma ◽  
Naca0012 Airfoil ◽  
Actuation Signal

An experimental study was conducted to evaluate the anti-icing performance of NS-DBD plasma actuator under the conditions of airflow speed U = 65 m/s, ambient temperature T = −10 °C, liquid water content LWC = 0.5 g/m3, mean-volume diameter MVD = 25 μm, mainly to clarify the effect of pulse frequency and voltage amplitude of actuation on anti-icing performance. A NACA0012 airfoil model with a chord length of c = 280 mm was used in the tests. The NS-DBD plasma actuator was mounted at the front part of the airfoil. A FLIR infrared (IR) imager and CCD camera were used to record the anti-icing process of the NS-DBD plasma actuator. Two typical discharge conditions were selected for the anti-icing experiments. The first was HV-LF discharge, corresponding to discharge under higher voltage amplitude with lower pulse frequency; the second was LV-HF discharge, corresponding to discharge under lower voltage amplitude with higher pulse frequency. Results reveal that NS-DBD is a very promising method for anti-icing. With the same power consumption, the LV-HF discharge shows a better anti-icing performance compared to HV-LF discharge under the same icing conditions. In view of pulse duration and duty circle, combined with heat dissipation, it is suggested that there is a threshold frequency, corresponding to the voltage amplitude of electric actuation signal and the incoming flow condition, to achieve effective anti-icing performance.

S0504-4-1 An Experimental Study on Acceleration Mechanism of Jet by DBD Plasma Actuator

2009 ◽  
Vol 2009.2 (0) ◽  
pp. 201-202
Author(s):  
Takehiko Segawa ◽  
Hiro Yoshida ◽  
Shinya Takekawa ◽  
Kwing-So Choi
Keyword(s):  
Experimental Study ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Acceleration Mechanism

Experimental Study on DBD Plasma Actuator with Combination of AC and Nanosecond Pulse Voltage

2011 ◽  
Vol 131 (8) ◽  
pp. 701-707 ◽  
Author(s):  
Taichi Kimura ◽  
Keisuke Udagawa(Takashima) ◽  
Hiroyuki Yamasaki
Keyword(s):  
Experimental Study ◽  
Plasma Actuator ◽  
Nanosecond Pulse ◽  
Pulse Voltage ◽  
Dbd Plasma

Experimental Study of DBD Plasma Actuator with Combination of AC and Nanosecond Pulse Voltage

2013 ◽  
Vol 185 (2) ◽  
pp. 21-29 ◽  
Author(s):  
Taichi Kimura ◽  
Keisuke Udagawa Takashima ◽  
Hiroyuki Yamasaki
Keyword(s):  
Experimental Study ◽  
Plasma Actuator ◽  
Nanosecond Pulse ◽  
Pulse Voltage ◽  
Dbd Plasma

Experimental Study on the Detailed Structure of Separation Bubble in Flow Control with DBD Plasma Actuator

2017 ◽  
Author(s):  
Yuma Miyakawa ◽  
Satoshi Sekimoto ◽  
Makoto Sato ◽  
Taku Nonomura ◽  
Akira Oyama ◽  
...  
Keyword(s):  
Experimental Study ◽  
Flow Control ◽  
Separation Bubble ◽  
Plasma Actuator ◽  
Detailed Structure ◽  
Dbd Plasma

Experimental Study of Effects of Frequency for Burst Wave on DBD Plasma Actuator for Separation Control

2011 ◽  
Author(s):  
Satoshi Sekimoto ◽  
Kengo Asada ◽  
Tatsuya Usami ◽  
Shinichiro Ito ◽  
Taku Nonomura ◽  
...  
Keyword(s):  
Experimental Study ◽  
Plasma Actuator ◽  
Separation Control ◽  
Dbd Plasma

Experimental Study of Blowing Direction Effects of DBD Plasma Actuator on Separation Control of Flow Around an Airfoil

2011 ◽  
Author(s):  
Taku Nonomura ◽  
Satoshi Sekimoto ◽  
Kengo Asada ◽  
Akira Oyama ◽  
Kozo Fujii
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Normal Mode ◽  
Separated Flow ◽  
Plasma Actuator ◽  
Velocity Fields ◽  
Separation Control ◽  
Dbd Plasma ◽  
Burst Mode ◽  
Piv Measurement

An experimental study of plasma actuator on separation control is conducted. The plasma actuator is used for control of separated flow around NACA0015 airfoil. The Reynolds number based on chord length is set to 60,000 and the angle of attack is set to 12[deg]. The plasma actuator is applied with normal mode and burst mode, where normal mode denotes continuous actuation and burst mode denotes temporary intermittent actuation. Also, actuations for co-flow blowing and counter blowing are conducted. The averaged pressure coefficients of wing surface and velocity fields are measured. For velocity fields, PIV measurement is adopted. Comparing counter and co-flow blowings of plasma actuator, the effects of counter blowing is investigated. Also, for both co-flow and counter blowing cases, we investigate the effects of burst mode. Through the series of experiments, following two types of mechanism for separation control will be discussed. One type is considered to be directly giving momentum in the boundary layer which seems to be more active in co-flow blowing with normal mode. The other type is considered to be enhancement of the mixing, leading to increase in momentum thickness of the boundary layer. The latter mechanism seems to be active in the burst mode with both co-flow and counter blowing.

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