Experimental investigation of the sound emission of skewed axial fans with leading-edge serrations

2019 ◽  
Author(s):  
Florian Krömer ◽  
Felix Czwielong ◽  
Stefan Becker
Keyword(s):  
Experimental Investigation ◽  
Leading Edge ◽  
Sound Emission ◽  
Axial Fans

Experimental Investigation of the Sound Emission of Skewed Axial Fans with Leading-Edge Serrations

AIAA Journal ◽  
2019 ◽  
Vol 57 (12) ◽  
pp. 5182-5196 ◽  
Author(s):  
Florian Krömer ◽  
Felix Czwielong ◽  
Stefan Becker
Keyword(s):  
Experimental Investigation ◽  
Leading Edge ◽  
Sound Emission ◽  
Axial Fans

Experimental Investigation of the Sound Reduction by Leading-Edge Serrations in Axial Fans

AIAA Journal ◽  
2018 ◽  
Vol 56 (5) ◽  
pp. 2086-2090 ◽  
Author(s):  
Florian Krömer ◽  
Andreas Renz ◽  
Stefan Becker
Keyword(s):  
Experimental Investigation ◽  
Leading Edge ◽  
Axial Fans ◽  
Sound Reduction

Experimental investigation of the effect of active flow control on the wake of a wind turbine blade

2021 ◽  
pp. 095440622110089
Author(s):  
GholamHossein Maleki ◽  
Ali Reza Davari ◽  
Mohammad Reza Soltani
Keyword(s):  
Experimental Investigation ◽  
Wind Turbine ◽  
Turbine Blade ◽  
Active Flow Control ◽  
Leading Edge ◽  
Wind Turbine Blade ◽  
Plasma Actuators ◽  
Plasma Actuation ◽  
Surface Pressure Distribution ◽  
Stall Angle

An extensive experimental investigation was conducted to study the effects of Dielectric Barrier Discharge (DBD), on the flow field of an airfoil at low Reynolds number. The DBD was mounted near the leading edge of a section of a wind turbine blade. It is believed that DBD can postpone the separation point on the airfoil by injecting momentum to the flow. The effects of steady actuations on the velocity profiles in the wake region have been investigated. The tests were performed at α = 4 to 36 degrees i.e. from low to deep stall angles of attack regions. Both surface pressure distribution and wake profile show remarkable improvement at high angles of attack, beyond the static stall angle of the airfoil when the plasma actuation was implemented. The drag calculated from the wake momentum deficit has further shown the favorable role of the plasma actuators to control the flow over the airfoil at incidences beyond the static stall angle of attack of this airfoil. The results demonstrated that DBD has been able to postpone the stall onset significantly. It has been observed that the best performance for the plasma actuation for this airfoil is in the deep stall angles of attack range. However, below and near the static stall angles of attack, plasma augmentation was pointed out to have a negligible improvement in the aerodynamic behavior.

Base-Vented Hydrofoils of Finite Span Under a Free Surface: An Experimental Investigation

1984 ◽  
Vol 28 (02) ◽  
pp. 90-106
Author(s):  
Jacques Verron ◽  
Jean-Marie Michel
Keyword(s):  
Experimental Investigation ◽  
Free Surface ◽  
Flow Rate ◽  
Cavity Length ◽  
Three Dimensional ◽  
Leading Edge ◽  
Pulsation Frequency ◽  
Cavity Pressure ◽  
Air Flow Rate ◽  
Cavity Configuration

Experimental results are given concerning the behavior of the flow around three-dimensional base-vented hydrofoils with wetted upper side. The influence of planform is given particular consideration so that the sections of the foils are simple wedges with rounded noses. Results concern cavity configuration, the relation between the air flow rate and cavity pressure, leading-edge cavitation, cavity length, pulsation frequency, and force coefficients.

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