Control of wall-separated flow by internal acoustic excitation

Hsiao, Fei‐Bin; Liu, Chin-Fung; Shyu, J.Y.; Wang, Muh-Rong

doi:10.2514/6.1989-974

Cited by 18 publications

(16 citation statements)

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“…Other active methods of controlling boundary layer separation and re-attachment include acoustic excitations (Huang et al 1987, Hsiao et al 1990, periodic forcing of the velocity field by means of an oscillating flap or wire (Koga et al 1984, Bar-Sever 1989, as well as many other techniques that will not be discussed herein. The publications by Lachman (1961) and Chang (1976) and the reviews by Gad-elHak (1990) and Gad-el-Hak and Bushnell (1991) provide extensive information and further references on this exciting topic.…”

Section: Flow Separation Controlmentioning

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: Flow Separation Controlmentioning

confidence: 99%

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

Rediniotis¹

2004

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“…In previous separation control studies, acoustic excitation (Hsiao et al 1990 andHuang et al 1987) seems facility dependent because the acoustic drivers stimulate the wind tunnel resonant modes to excite the separated flow; oscillatory blowing valves (Allen et al 2000) appear to have slow dynamic response; active flexible wall transducers (Sinha 2001) have complicated structures despite its high actuation efficiency and ability to actuate and sense with the same hardware. These drawbacks have limited the use of these actuators.…”

Section: Closed-loop Separation Controlmentioning

confidence: 99%

“…Internal acoustic excitation (Hsiao et al 1990;Huang et al 1987), speakers , oscillatory blowing valves (Allen et al 2000), and MEMS-based actuators (Rathnasingham and Breuer 2003), etc. have been investigated.…”

Section: Overviewmentioning

confidence: 99%

Separation Control Using ZNMF Devices: Flow Physics and Scaling Laws

Tian¹,

Cattafesta²

2007

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20080604029 REPORT DOCUMENTATION PAGE Form Approved I OMB No. 0704-0188Public reporting burden for this collection of information is estimated to average hour per response, including the time for reviewing instructions, searching data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to

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“…It has been shown that the separating shear layer over stalled 2-and 3-D aerodynamic surfaces is typically dominated by a strong coupling to the instability of the near wake (e.g., Wu et al 1998). Traditional separation control strategy uses actuation coupling to the narrow-band receptivity of the separating flow at the unstable Strouhal numbers of the near wake (e.g., St D ~ O(1), Hsiao et al 1990, Neuberger and Wygnanski 1987, Williams et al 1991, Chang et al 1992, Seifert et al 1993). An alternative approach uses actuation at substantially higher frequencies to decouple the global flow instabilities from fluidic modification of the "apparent" aerodynamic shape of the body (e.g., St D » O(1), Erk 1997, Smith et al 1998, Amitay et al 2001, Honohan et al 2000, Glezer et al 2005.…”

Section: Technical Backgroundmentioning

confidence: 99%

Unsteady Aerodynamic Flow Control of Moving Platforms

Glezer¹

2014

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Control of wall-separated flow by internal acoustic excitation

Cited by 18 publications

References 0 publications

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

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

Separation Control Using ZNMF Devices: Flow Physics and Scaling Laws

Unsteady Aerodynamic Flow Control of Moving Platforms

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