Control of Flow Separation and Its Associated Physics on a NACA0015 Using Synthetic Jet Actuators

2006 ◽  
Author(s):  
Wei Long Siauw ◽  
Jean Tensi ◽  
Se´bastien Bourgois ◽  
Jean-Paul Bonnet ◽  
Jean-Marc Breux ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Flow Separation ◽  
Laser Light ◽  
Laser Sheet ◽  
Synthetic Jet ◽  
Chord Length ◽  
Flow Physics ◽  
Synthetic Jet Actuators ◽  
Jet Actuators

Wind tunnel flow control experiments are conducted on two NACA0015 airfoil models, one of which having a chord length of 1.0m and the other having a chord of 0.35m, with the aim of exploring the separated flow physics and delaying flow separation. The larger model is tested in a low speed wind tunnel, measuring 1.25m by 1.25m at a Reynolds number of 0.4 and 0.27 million. This model is used to provide a quick proof of concept concerning the efficiency of various synthetic jet designs. Laser light visualization and Particle Image Velocimetry (PIV) studies are performed on this model. The synthetic jet actuators implemented (mechanically and acoustically generated) is realized through holes (2 and 3mm in diameter). The actuators are positioned at 20% or 70% of chord length from the leading edge for controlling separation at incidences between 12° and 15°. Flow separation delay and reattachment, depending on the frequency and momentum of the synthetic jet are observed qualitatively via laser sheet visualization in all cases. The efficiency of the actuator is quantified via the extent of separation observed with the PIV measurements. The technique of Proper Orthogonal Decomposition (POD) is applied to further reveal the large eddies in the separated shear layer and its interaction with the boundary layer. The smaller model is tested in a larger wind tunnel measuring 2.4m by 2.6m at a Reynolds number of 0.9 million. This is a more realistic flow condition with minimal wall and aspect ratio influence as compared to the larger model. The main experimental objective concerning this model is to quantify the baseline aerodynamic of the NACA0015 before implementation of synthetic jets. Laser light and surface oil visualizations are performed. Measurements concerning surface pressure and wake velocity characteristics are also made for this model. The lift of which is estimated via the integration of surface static pressure and the drag is estimated by wake survey technique using a pitot tube that is made to traverse in the wake. In addition, time resolved data are obtained in the wake of the airfoil by means of hotwires. Both hotwire measurement reveal typical Strouhal number of 0.34–0.4. These results are extrapolated to the large airfoil for interpretation of the flow physics during control. To sum up, the main results in the current study highlight the characteristics of the baseline airfoil and the ability of synthetic jet actuator techniques to obtain significant delay of the separation.

Low Reynolds Number Flow Control Over an Airfoil Using Synthetic Jet Actuators

2010 ◽  
Author(s):  
Sebastian D. Goodfellow ◽  
Serhiy Yarusevych ◽  
Pierre Sullivan
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Flow Visualization ◽  
Low Reynolds Number ◽  
Excitation Frequency ◽  
Synthetic Jet ◽  
Hot Wire ◽  
Synthetic Jet Actuators ◽  
Jet Actuators ◽  
Low Reynolds

The influence of periodic excitation from synthetic jet actuators, SJA, on boundary layer separation and reattachment over a NACA 0025 airfoil at a low Reynolds number is studied. All experiments were performed in a low-turbulence recirculating wind tunnel at a Reynolds number of 100000 and angle of attack of α = 0°. Mounted just below the surface of the airfoil, the SJA consists of four (32.77mm diameter) piezo-electric ceramic diaphragms positioned in a single row. Flow visualization and hot wire tests were conducted with the SJA outside of the airfoil to characterize the exit flow. Results from flow visualization show a vertical jet pulse accompanied by two counter rotating vortices being produced at the exit of the simulated slot, with the vortices shed at the excitation frequency. Based on flow visualization results, the length scales of successive vortices were used to estimate the exit velocities. Hot-wire measurements determined the maximum jet velocity for a range of excitation frequencies (f = 50Hz–2.7kHz) and voltages (Vp–p = 50V–300V), which was used to characterize the excitation amplitude in terms of the momentum coefficient (cμ). With the SJA installed in the airfoil, preliminary flow visualization results show a reattachment of the boundary layer and a significant reduction in wake width.

A New Class of Synthetic Jet Actuators—Part I: Design, Fabrication and Bench Top Characterization

2005 ◽  
Vol 127 (2) ◽  
pp. 367-376 ◽  
Author(s):  
J. L. Gilarranz ◽  
L. W. Traub ◽  
O. K. Rediniotis
Keyword(s):  
Flow Separation ◽  
Synthetic Jet ◽  
Synthetic Jets ◽  
Flow Separation Control ◽  
Synthetic Jet Actuators ◽  
New Class ◽  
Momentum Coefficient ◽  
Jet Actuators ◽  
In Series ◽  
Exit Slot

Although the potential of synthetic jets as flow separation control actuators has been demonstrated in the existing literature, there is a large gap between the synthetic jet actuators (SJA) used in laboratory demonstrations and the SJAs needed in realistic, full-scale applications, in terms of compactness, weight, efficiency, control authority and power density. In most cases, the SJAs used in demonstrations are either too large or too weak for realistic applications. In this work, we present the development of a new class of high-power synthetic jet actuators for realistic flow control applications. The operating principle of the actuator is the same as that of crankshaft driven piston engines, which makes a significant part of the technology necessary for the actuator development available off-the-shelf. The design of the actuator is modular and scalable. Several “building block” units can be stacked in series to create the actuator of the desired size. Moreover, active exit slot reconfiguration, in the form of variable exit slot width, decouples the actuator frequency from the actuator jet momentum coefficient and allows the user to set the two independently (within limits). Part I of this paper presents the design, fabrication and bench top characterization of the actuator. Several versions of the actuator were designed, built and tested, leading up to the development of a six-piston compact actuator that has a maximum power consumption of 1200 W (1.6 hp) and can produce (for the tested conditions) peak exit velocities as high as 124 m/s. In Part II, the actuator was housed in the interior of a NACA0015 profiled wing with a chord of 0.375 m (14.75 inches). The assembly’s performance in controlling flow separation was studied in the wind tunnel.

Wind tunnel quantification of dynamic stall on an S817 airfoil and its control using synthetic jet actuators

Wind Energy ◽  
2018 ◽  
Vol 22 (1) ◽  
pp. 21-33 ◽  
Author(s):  
Thomas T. Rice ◽  
Keith Taylor ◽  
Michael Amitay
Keyword(s):  
Wind Tunnel ◽  
Synthetic Jet ◽  
Dynamic Stall ◽  
Synthetic Jet Actuators ◽  
Jet Actuators

scholarly journals Impact of the Confinement Plate on the Velocity of Synthetic Jet

Actuators ◽  
2021 ◽  
Vol 10 (9) ◽  
pp. 208
Author(s):  
Emil Smyk ◽  
Robert Smusz
Keyword(s):  
Reynolds Number ◽  
Velocity Profile ◽  
Stokes Number ◽  
Synthetic Jet ◽  
Velocity Measurements ◽  
Synthetic Jet Actuators ◽  
Axial Velocity Profile ◽  
Jet Actuators ◽  
Constant Temperature Anemometer ◽  
The Impact

In the paper, the impact of the limitation of the environment around the office of synthetic jet actuators were tested. One short and three length orifices were tested and compared with and without confinement plate. In total, seven different synthetic jet actuators were investigated. The constant temperature anemometer was used for the velocity measurements. The synthetic jet was tested for the Reynolds number in the range of 2300 < Re < 19,500, and the Stokes number in the range of 46 < S < 62. The confinement plate decreased the velocity of synthetic jet depending on the actuator supply power even around 5%. However, the differences in axial velocity profile are slight and the impact of the confinement plate was visible only in the distance x/d < 4.

Experimental Study on the Use of Synthetic Jet Actuators for Lift Control

2016 ◽  
Author(s):  
Ricardo B. Torres ◽  
Gustaaf B. Jacobs ◽  
Michael J. Cave
Keyword(s):  
Experimental Study ◽  
Reynolds Number ◽  
Shear Layer ◽  
Synthetic Jet ◽  
Inlet Guide Vane ◽  
Trailing Edge ◽  
Synthetic Jet Actuator ◽  
Synthetic Jet Actuators ◽  
Jet Actuators ◽  
Lift Control

An experimental study on the use of synthetic jet actuators for lift control on a generic compressor airfoil is conducted. A wind tunnel model of a NACA 65(2)-415 airfoil, representative of the cross section of an Inlet Guide Vane (IGV) in an industrial gas compressor, is 3D-printed. Nine synthetic jet actuators are integrated within a planar wing section with their slots covering 61% of pressure side of the airfoil span, located 13% chord upstream of the trailing edge. The Helmholtz frequency of the slot is matched closely with the piezoelectric element material frequency. The slot is designed so that the bi-morph actuation creates a jet normal to the airfoil surface. By redirecting or vectoring the shear layer at the trailing edge, the synthetic jet actuator increases lift and decreases drag on the airfoil without a mechanical device or flap. Tests are performed at multiple Reynolds number ranging from Re=150,000 to Re=450,000. The increased lift of the integrated synthetic jet actuator is dependent on the Reynolds number and free stream velocity, the actuation frequency, and angle of attack. For actuation at 1450 Hz the synthetic jet actuator increases lift up to 7%. The synthetic jet increases L/D up to 15%. Velocity contours obtained through PIV show that the synthetic jet turns the trailing edge shear layer similar to a Gurney flap.

Control of internal flow separation using synthetic jet actuators

2000 ◽  
Author(s):  
M. Amitay ◽  
D. Parekh ◽  
D. Pitt ◽  
V. Kibens ◽  
A. Glezer
Keyword(s):  
Flow Separation ◽  
Internal Flow ◽  
Synthetic Jet ◽  
Synthetic Jet Actuators ◽  
Jet Actuators

scholarly journals Synthetic Jet Actuators with the Same Cross-Sectional Area Orifices-Flow and Acoustic Aspects

2021 ◽  
Vol 11 (10) ◽  
pp. 4600
Author(s):  
Emil Smyk ◽  
Joanna Wilk ◽  
Marek Markowicz
Keyword(s):  
Reynolds Number ◽  
Force Measurement ◽  
Reaction Force ◽  
Synthetic Jet ◽  
Cross Sectional ◽  
Synthetic Jet Actuators ◽  
Cross Section Area ◽  
Section Area ◽  
Jet Actuators ◽  
Measurement Results

In this paper, synthetic jet actuators (SJAs) with three different orifice shapes (circular, square, and slot) with the same cross-section area were investigated. The SJA efficiency and the synthetic jet (SJ) Reynolds number were calculated based on the time-mean reaction force measurement. The momentum velocity was measured with hot-wire anemometry and additionally, the sound pressure level (SPL) was measured. The efficiency was equal maximally to 5.3% for each orifice shape, but the square orifice characterized the higher Reynolds number. The compared centerline (axial) velocities and the radial velocity profile at a distance of 112 mm were similar for each orifice type. The SPL measurement results were surprisingly constant in relation to each other. The square orifice generates the lowest SPL, approximately 2.8dB lower than the circular orifice, and approximately 4.2dB lower than the slot orifice, at each investigated real power. Finally, the differences to other papers and limitations of the approach to comparing orifices presented in the present paper were indicated.

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