Parametric and dynamic modeling for synthetic jet control of a post-stall airfoil

He, Yanyu; Cary, Andrew W.; Peters, David A.

doi:10.2514/6.2001-733

Cited by 24 publications

(12 citation statements)

References 8 publications

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“…In the recent years a large amount of numerical computations and simulations has been produced in the area of flow separation control over lifting surfaces via synthetic jet actuators (Donovan et al, 1998, Hassan and Munts, 2000, He and Krai, 2000, and He et al, 2001. Another application of synthetic jet technology is the control of the aerodynamic performance of lifting surfaces through fluidic modifications of their apparent aerodynamic shape , Honohan et al, 2000, Parekh and Glezer, 2000.…”

Section: Synthetic Jet Actuators (Sjas)mentioning

confidence: 99%

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Rediniotis¹

2004

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the tir gathering and maintaining the data needed, and completing and reviewing the collection of information. Send commenjs regi of information, including suggestions for reducing the burden, PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Texas Engineering Experiment Station Texas A&M University CoUege Station Texas 77843-3141 This work presents an investigation of synthetic jet actuation for separation control over wings/airfoils, in steady and unsteady flows, the development of hi^-power, compact synthetic jet actuators (SJA) for flow separation control, the modelmg and control of such actuators and the modeling and control of the resulting SJA-controUed aerodynamics and wing/airfoil, respectively. The developed actuator is compact enough to fit in the interior of a NACA0015 profiled wing with a chord of 0.375 m. Test bench experiments showed that the multi-piston actuator array was capable of producing exit velocities of up to 90 m/s for an actuator frequency of 130 Hz. The actuator was placed in a NACA 0015 wmg and tested m a wmd tunnel. An experimental investigation into the effects of a synthetic jet actuator on the performance of the wing, in steady flow, is described. Emphasis is placed on the capabilities of the actoator to control the separation of the flow over the wing at high angles of attack. The investigation included the use of force balance measurements, on -surface flow visualization with oil and tufts, off-surface flow vBualizations with smoke, surface pressure distribution measurements and wake surveys. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)USAF

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Section: Synthetic Jet Actuators (Sjas)mentioning

confidence: 99%

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Rediniotis¹

2004

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“…This is typical of a bluff body flow, and studies in this field typically focus on the latter frequency and not the former. [17][18][19] Only Wu et al 20 consider both parameters. When the mean flow reattaches, there can be a third natural frequency, associated with the shedding of the separation bubble.…”

Section: B Difficulties In Finding An Optimal Forcing Frequencymentioning

confidence: 99%

Koopman spectral analysis of separated flow over a finite-thickness flat plate with elliptical leading edge

Rowley

Aram

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The separated flow over an airfoil is characterized by up to three distinct natural frequencies: those of the shear layer, separation bubble, and wake. Previous work has shown that open-loop forcing at sub-and super-harmonics of these frequencies can be especially effective in controlling the extent of the separation bubble. Unfortunately, an understanding of the mechanisms driving this behavior is far from complete. In this work, we investigate the interactions between the shear layer and wake using a combination of direct numerical simulations and spectral analysis. We simulate the forced and unforced flows over a finite-thickness flat plate using an immersed boundary method. Spectral analysis of the resulting dynamics is performed using the Koopman operator, a linear operator applicable even to nonlinear systems, as well as traditional signal processing techniques. Using these two approaches, we identify pertinent flow structures based on their frequency content and posit the nature of their interactions. Nomenclature U ∞ freestream velocity, defined at upstream boundary of domain t thickness of flat plate c chord length of flat plate x/c distance from leading edge, measured in chord lengths v j average velocity of synthetic jet during expulsion phase d j width of synthetic jet slot C μ =v 2 j d j /U 2 ∞ c momentum coefficient for synthetic jet F + = f c/U ∞ nondimensional frequency d w width of wake St = f d w /U ∞ Strouhal number PSD power spectral density

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“…As a result, the investigations of the synthetic jet on rotor are still theoretic at present. Additionally, there are still some problems which have not been overcome in the applications of synthetic jets on airfoil (23) , such as the choice of the jet parameters (24,25) .…”

Section: Introductionmentioning

confidence: 99%

Experimental analyses of synthetic jet control effects on aerodynamic characteristics of helicopter rotor

Zhao

Chen

et al. 2020

Aeronaut. j.

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Experimental analyses of synthetic jet control (SJC) effects on aerodynamic characteristics of rotor in steady state and in hover were conducted. To ensure the structural strength of rotor and enough interior space for holding the synthetic jet actuators (SJAs), a particular blade with a frame-covering structure was designed and processed, and the experiment was conducted with low free stream velocities and rotor rotation speeds. There were three test conditions. In steady state, there were three free stream velocities (10m/s, 15m/s and 20m/s). In hover state, the rotor was worked with two rotation speeds of 180RPM and 240RPM. In forward flight, the rotor was worked with a rotation speed of 180RPM and a free stream velocity of 7.5m/s. To measure the synthetic jet control effect on rotor in stall, the range of collective pitch was set from 10° to 28° in steady state. The aerodynamic forces and sectional velocity field were measured by using the six-component balance and the Particle Image Velocimetry (PIV) system in the wind tunnel. Flow control effects on the blade based on the synthetic jets (SJ) were experimentally investigated with different jet parameters, such as jet locations, jet angles, and jet velocities. In steady state, the jet closer to the leading edge, and the jet angle of 90° had more advantages in improving the aerodynamic characteristics. Furthermore, the aerodynamic forces and sectional velocity field measurement of rotor in hover were conducted, it showed that SJAs could increase flow velocity at the upper surface, which led to lower upper surface pressure. As a result, the normal forces of rotor with two rotation speeds were increased significantly. These results indicated that the synthetic jet has a capability of increasing the normal force and delaying or preventing the stall of rotor.

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Parametric and dynamic modeling for synthetic jet control of a post-stall airfoil

Cited by 24 publications

References 8 publications

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Koopman spectral analysis of separated flow over a finite-thickness flat plate with elliptical leading edge

Experimental analyses of synthetic jet control effects on aerodynamic characteristics of helicopter rotor

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