An Experimental Investigation of Jet and Vortex Actuator for Active Flow Control

2008 ◽  
Author(s):  
Hasan Gunes ◽  
Sertac Cadirci ◽  
Ulrich Rist
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Active Flow Control ◽  
Active Flow

Experimental Investigation of Endwall and Suction Side Blowing in a Highly Loaded Compressor Stator Cascade

2010 ◽  
Author(s):  
Daniel Nerger ◽  
Horst Saathoff ◽  
Rolf Radespiel ◽  
Volker Gu¨mmer ◽  
Carsten Clemen
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Control Method ◽  
Active Flow Control ◽  
Pressure Rise ◽  
Suction Side ◽  
Spanwise Direction ◽  
Flow Power ◽  
Active Flow ◽  
Highly Loaded

The following paper describes an experimental investigation of a highly loaded stator cascade with a pitch to chord ratio of t/l = 0.6. Experiments without as well as with active flow control by means of endwall and suction side blowing were conducted. Five-hole-probe measurements in pitchwise and spanwise direction as well as endwall oil flow visualizations were carried out in order to determine the performance of the cascade and to analyze the flow phenomena occuring. To quantify the effectivity of the active flow control method, taking the additional energy input into account, corrected losses and an efficiency, which relates the difference of flow power deficit with and without active flow control to the flow power of the blowing jet itself, were evaluated. Even though an increase of static pressure rise could be achieved, a decrease of the total pressure losses was possible for a few operating points only.

Helicopter Fuselage Model Drag Reduction by Active Flow Control Systems

2019 ◽  
Vol 64 (2) ◽  
pp. 1-15 ◽  
Author(s):  
Fabrizio De Gregorio
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Control Systems ◽  
Flow Separation ◽  
Laboratory Tests ◽  
Active Flow Control ◽  
Aerodynamic Characteristics ◽  
Pulsed Jets ◽  
Wide Range ◽  
Active Flow

A comprehensive experimental investigation of a helicopter blunt fuselage model was carried out to evaluate the effectiveness of active flow control (AFC) systems in reducing parasite fuselage drag. The main objective was to demonstrate the capability of different active technologies to decrease fuselage drag by alleviating the flow separation in the loading ramp region of large transport helicopters. The work was performed on a simplified blunt fuselage at model scale. Two different flow control actuators were considered for evaluation: steady blowing and unsteady blowing (i. e., pulsed jets). Laboratory tests of each individual actuator were performed to assess their performance and properties. The fuselage model was investigated with and without the AFC systems located along the loading ramp edges. Significant drag reductions were achieved for a wide range of fuselage angles of attack and sideslip angles without negatively affecting other aerodynamic characteristics.

Experimental Investigation of Endwall and Suction Side Blowing in a Highly Loaded Compressor Stator Cascade

2011 ◽  
Vol 134 (2) ◽  
Author(s):  
Daniel Nerger ◽  
Horst Saathoff ◽  
Rolf Radespiel ◽  
Volker Gümmer ◽  
Carsten Clemen
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Control Method ◽  
Active Flow Control ◽  
Pressure Rise ◽  
Suction Side ◽  
Additional Energy ◽  
Flow Power ◽  
Active Flow ◽  
Highly Loaded

The following paper describes an experimental investigation of a highly loaded stator cascade with a pitch to chord ratio of t/l=0.6. Experiments without as well as with active flow control by means of endwall and suction side blowing were conducted. Five-hole-probe measurements in pitchwise and spanwise directions as well as endwall oil flow visualizations were carried out in order to determine the performance of the cascade and to analyze the flow phenomena occurring. To quantify the effectivity of the active flow control method, taking the additional energy input into account, corrected losses and an efficiency, which relates the difference of flow power deficit with and without active flow control to the flow power of the blowing jet itself, were evaluated. Even though an increase of static pressure rise could be achieved, a decrease of the total pressure losses was possible for a few operating points only.

Experimental Investigation on Stall Separation Control on NACA0015 Airfoil by Steady Plasma Aerodynamic Actuation

2012 ◽  
Vol 516-517 ◽  
pp. 726-730 ◽  
Author(s):  
Min Sun ◽  
Bo Yang ◽  
Jian Min Li ◽  
Ming Kai Lei
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Free Stream ◽  
Active Flow Control ◽  
Lift Coefficient ◽  
Actuation Voltage ◽  
Control Effectiveness ◽  
Plasma Flow Control ◽  
Stall Angle ◽  
Active Flow

Experimental investigation was performed to study the influence law of the free-stream speed, angle of attack and actuation voltage on the control effectiveness of NACA0015 airfoil stall separation suppression by steady plasma aerodynamic actuation. It is found that plasma actuation can effectively suppress flow separation on the airfoil at free-stream speeds in the range from 20 m/s up to 65 m/s. When the speed is 25m/s, the stall angle will be delayed by 3°, lift coefficient will increase and drag coefficient will decrease by 10.4% and 28.9% respectively. Moreover, Experimental results indicate that the threshold voltage increases with the increasing free-stream speed and attack angle. Meanwhile, both of smoke flow visualization and flow control experiments were carried out, conclusions show that the direction of induce flow has little effect on plasma flow control effectiveness, which means that momentum transferring is not the basic cause of active flow control of plasma aerodynamic actuation.

Helicopter Fuselage Drag Reduction Using Active Flow Control: A Comprehensive Experimental Investigation

2015 ◽  
Vol 60 (3) ◽  
pp. 1-12 ◽  
Author(s):  
A. Le Pape ◽  
C. Lienard ◽  
C. Verbeke ◽  
M. Pruvost ◽  
J.-L. De Coninck
Keyword(s):  
Experimental Investigation ◽  
Drag Reduction ◽  
Flow Control ◽  
Active Flow Control ◽  
Active Flow
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