Characterization of a compact, high-power synthetic jet actuator for flow separation control

2002 ◽  
Author(s):  
O. Rediniotis ◽  
J. Gilarranz ◽  
L. Traub
Keyword(s):  
Flow Separation ◽  
High Power ◽  
Synthetic Jet ◽  
Separation Control ◽  
Flow Separation Control ◽  
Synthetic Jet Actuator

Development of design methodology for a synthetic jet actuator array for flow separation control applications

2011 ◽  
Vol 227 (1) ◽  
pp. 110-124 ◽  
Author(s):  
Mark Jabbal ◽  
Stephen Liddle ◽  
Jonathan Potts ◽  
William Crowther
Keyword(s):  
Flow Separation ◽  
Synthetic Jet ◽  
Lessons Learned ◽  
Chamber Pressure ◽  
Bench Test ◽  
Separation Control ◽  
Control Applications ◽  
Flow Separation Control ◽  
Synthetic Jet Actuator ◽  
Tunnel Model

This article documents the development of synthetic jet actuator array hardware to augment high-lift system effectiveness in a wind tunnel model. The study involved the design, manufacture and bench test of a synthetic jet actuator array based on an inclined actuator configuration to reduce volume installation requirements without a loss in jet velocity relative to a non-inclined baseline model; incorporation of proper synthetic jet actuator systems wiring and internal synthetic jet actuator chamber pressure-sensing for actuator health monitoring. The peak velocity obtained from the inclined synthetic jet actuator array was 100 m/s, which favourably compares to the baseline array (∼90 m/s), while reducing the usable depth requirements by 50%. The final outcome of this study has been to apply the design lessons learned to develop a methodology for designing a synthetic jet actuator array with the constraints of using piezoelectric-based actuator technology for flow separation control applications.

Estimation of the momentum coefficient of synthetic jet in flow separation control over an airfoil

2020 ◽  
Vol 234 (14) ◽  
pp. 2050-2061
Author(s):  
Zhiyong Liu ◽  
Zhenbing Luo ◽  
Yan Zhou ◽  
Shiqing Li ◽  
Pan Cheng
Keyword(s):  
Flow Separation ◽  
Estimation Method ◽  
Synthetic Jet ◽  
Separation Point ◽  
Separation Control ◽  
Injection Angle ◽  
Flow Separation Control ◽  
Synthetic Jet Actuator ◽  
Momentum Coefficient ◽  
Stall Angle

A simple estimation method of momentum coefficient of synthetic jet actuator has been proposed. Flow separation over an airfoil can be suppressed sufficiently with the estimated momentum coefficient. At a certain angle of attack (AOA), momentum deficit of boundary layer at front of separation point can be quantified based on Bernoulli's theorem. The function of synthetic jet actuator is deemed to be momentum addition and two stages of the addition corresponding to blowing and suction phases are considered respectively. The required momentum coefficient as well as the associated injection angle is determined preliminarily with the assumption of synthetic jet actuator at front of separation point. Since synthetic jet actuator is usually installed near the leading edge, a modification is introduced to consider the influence of excitation location. Using this method, flow separation over a NACA0015 airfoil is suppressed nearly completely with AOA = 15° and synthetic jet actuator at x/ c = 10%. Different angle of attacks corresponding to pre-stall angle, post-stall angle, and deep stall angle have been examined, respectively. Results indicate that the method is effective at pre-stall angle and post-stall angle. However, momentum coefficient will be underestimated when the separation point is upstream to the location of the airfoil's maximum thickness. At deep stall angle, the method is invalid. The estimation method is useful for practices of flow separation control with synthetic jet actuator.

A New Class of Synthetic Jet Actuators—Part II: Application to Flow Separation Control

2005 ◽  
Vol 127 (2) ◽  
pp. 377-387 ◽  
Author(s):  
J. L. Gilarranz ◽  
L. W. Traub ◽  
O. K. Rediniotis
Keyword(s):  
Flow Separation ◽  
Lift Coefficient ◽  
Surface Flow ◽  
Synthetic Jet ◽  
Force Balance ◽  
Separation Control ◽  
Stream Velocity ◽  
Moderate Amount ◽  
Flow Separation Control ◽  
Synthetic Jet Actuator

In this work we present the application of the new synthetic jet actuator (SJA) to flow separation control over a NACA 0015 wing. The actuator is compact enough to fit in the interior of the wing that has a chord of 0.375 m. The wing was tested in the Texas A&M University Aerospace Engineering 3 ft×4 ft wind tunnel. An experimental investigation into the effects of the synthetic jet actuator on the performance of the wing is described. Emphasis is placed on the capabilities of the actuator to control the separation of the flow over the wing at high angles of attack. The results include force balance measurements, on surface and off surface flow visualization, surface pressure measurements, and wake surveys. All of the reported tests were performed at a free-stream velocity of 35 m/s, corresponding to a Reynolds number of 8.96×105. The angle of attack was varied from −2.0 deg to 29.0 deg. For the results presented, at angles of attack lower than 10 deg, the actuator has minimal effects. At higher angles of attack, the SJA delays the onset of stall. The use of the actuator causes an 80% increase in the maximum lift coefficient, while the angle at which stall occurs is increased from 12 to 18 deg. The drag on the wing is decreased as a consequence of SJA actuation. For angles of attack larger than 18 deg, where the wing experiences massive separation, the SJA still provides a moderate amount of lift augmentation compared to the unforced case. At angles of attack larger than 25°, a larger frequency of actuation is required to produce significant effects.

Flow separation control via synthetic jet actuation

2000 ◽  
Author(s):  
P. Rao ◽  
J. Gilarranz ◽  
J. Ko ◽  
T. Strganac ◽  
O. Rediniotis
Keyword(s):  
Flow Separation ◽  
Synthetic Jet ◽  
Separation Control ◽  
Flow Separation Control
Sign in / Sign up

Export Citation Format

Share Document