An experimental study on the thermal characteristics of NS-DBD plasma actuation and application for aircraft icing mitigation

It is well known that attaching fins on the tubes surfaces can enhance the heat transfer into and out from the phase change materials (PCMs). This paper presents the results of an experimental study on the thermal characteristics of finned coil latent heat storage unit (LHSU) using paraffin as the phase change material (PCM). The paraffin LHSU is a rectangular cube consists of continuous horizontal multibended tubes attached vertical fins at the pitches of 2.5, 5.0, and 7.5 mm that creates the heat transfer surface. The shell side along with the space around the tubes and fins is filled with the material RT54 allocated to store energy of water, which flows inside the tubes as heat transfer fluid (HTF). The measurement is carried out under four different water flow rates: 1.01, 1.30, 1.50, and 1.70 L/min in the charging and discharging process, respectively. The temperature of paraffin and water, charging and discharging wattage, and heat transfer coefficient are plotted in relation to the working time and water flow rate.

Download Full-text

Preparation and experimental study on the thermal characteristics of lightweight prefabricated nano-silica aerogel foam concrete wallboards

Construction and Building Materials ◽

10.1016/j.conbuildmat.2020.121895 ◽

2021 ◽

Vol 272 ◽

pp. 121895

Author(s):

Peng Liu ◽

Yan Feng Gong ◽

Guo Hua Tian ◽

Zheng Kun Miao

Keyword(s):

Experimental Study ◽

Silica Aerogel ◽

Thermal Characteristics ◽

Nano Silica ◽

Foam Concrete

Download Full-text

Experimental Study on Thermal Characteristics of DC Arc Formation between Ice-Electrode Gap

IEEE Transactions on Dielectrics and Electrical Insulation ◽

10.1109/tdei.2021.009546 ◽

2021 ◽

Vol 28 (5) ◽

pp. 1497-1505

Author(s):

Meng Wei ◽

Jianlin Hu ◽

Xiaofeng Wang ◽

Xingliang Jiang ◽

Ruihe Zhang ◽

...

Keyword(s):

Experimental Study ◽

Thermal Characteristics ◽

Electrode Gap ◽

Dc Arc

Download Full-text

Plasma actuation effect on a NACA 4412 airfoil

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-04-2021-0101 ◽

2021 ◽

Vol ahead-of-print (ahead-of-print) ◽

Author(s):

Burak Karadag ◽

Cem Kolbakir ◽

Ahmet Selim Durna

Keyword(s):

Reynolds Number ◽

Flow Separation ◽

Open Loop ◽

Electrode Configuration ◽

Small Scale ◽

Low Velocity ◽

Dbd Plasma ◽

Content Type ◽

Plasma Actuation ◽

Electric Wind

Purpose This paper aims to investigate the effects of a dielectric barrier discharge (DBD) plasma actuator (PA) qualitatively on aerodynamic characteristics of a 3 D-printed NACA 4412 airfoil model. Design/methodology/approach Airflow visualization study was performed at a Reynolds number of 35,000 in a small-scale open-loop wind tunnel. The effect of plasma actuation on flow separation was compared for the DBD PA with four different electrode configurations at 10°, 20° and 30° angles of attack. Findings Plasma activation may delay the onset of flow separation up to 6° and decreases the boundary layer thickness. The effects of plasma diminish as the angle of attack increases. Streamwise electrode configuration, in which electric wind is produced in a direction perpendicular to the freestream, is more effective in the reattachment of the airflow compared to the spanwise electrode configuration, in which the electric wind and the free stream are in the same direction. Practical implications The Reynolds number is much smaller than that in cruise aircraft conditions; however, the results are promising for low-velocity subsonic airflows such as improving control capabilities of unmanned aerial vehicles. Originality/value Superior efficacy of spanwise-generated electric wind over streamwise-generated one is demonstrated at a very low Reynolds number. The results in the plasma aerodynamics literature can be reproduced using ultra-low-cost off-the-shelf components. This is important because high voltage power amplifiers that are frequently encountered in the literature may be prohibitively expensive especially for resource-limited university aerodynamics laboratories.

Download Full-text