Adaptive Feedback Control of Flow Separation

Tian, Yuan; Song, Qi; Cattafesta, Louis N.

doi:10.2514/6.2006-3016

Cited by 34 publications

(24 citation statements)

References 11 publications

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“…In majority, these studies target the steady or quasi-steady state performance of lift enhancement and drag reduction at relatively low chord Reynolds number (typically <0.5 million). Closed-loop airfoil separation control has been studied at relatively low Reynolds number by Tian et al (2006) and Pinier et al (2007), and on a generic separated configuration at a chord Reynolds number of 16 million by Allan et al (2000). Detailed studies concerning the transient process of flow attachment and separation in response to a synthetic jet actuator have been performed by Darabi and Wygnanski (2004a,b), and Glezer (2002a, 2006).…”

Section: Introductionmentioning

confidence: 99%

Transient dynamics of the flow around a NACA 0015 airfoil using fluidic vortex generators

Siauw

Bonnet

Tensi

et al. 2010

International Journal of Heat and Fluid Flow

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Section: Introductionmentioning

confidence: 99%

Transient dynamics of the flow around a NACA 0015 airfoil using fluidic vortex generators

Siauw

Bonnet

Tensi

et al. 2010

International Journal of Heat and Fluid Flow

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“…Figure 19(b) presents the skewness evolution at x/c = 0.239 for deflection angles from 10 to 35 • (i.e. 10,16,18,20,22,24,26,28,30,35). Flap deflection has no effect on skewness evolution from 10 to 16 • .…”

Section: A Flow System Static Mapmentioning

confidence: 98%

“…Both coefficients can be optimized in the same time as proposed by Tian et al 21 whose closed-loop algorithm minimizes the drag-to-lift ratio. Tian et al 22 try to reduce the pressure fluctuations measured by unsteady pressure sensors which are integrated in a NACA 0025 airfoil. The feedback used by Benard et al 2 to control a NACA 0015 airfoil by means of plasma actuators is the on-surface static pressure of a single sensor located close to the leading edge.…”

Section: Introductionmentioning

confidence: 99%

Experimental Detection and Pulsed Jets Control of Turbulent Boundary Layer Separation

Chabert¹,

Dandois²,

Garnier³

et al. 2012

6th AIAA Flow Control Conference

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Wind tunnel experiments are conducted to investigate the effect of constant and periodic blowing on flow separation from a non-slotted NACA-type flap which is equipped with seven pulsed jets actuators and tested at Re 10 6 through different deflection angles from 2 to 35 • . Laser beam tomoscopy is first used to visualize flow structures with and without flow control. The recirculation zone length is mainly estimated by means of wall shear stress measurements provided by hot-film gauges which are chordwise distributed on the flap. Two separation criteria based on higher-order statistical moments are proposed to detect the flow separation location. They are practised in the uncontrolled, constant blowing and periodic blowing cases. The two criteria are finally applied to follow the open-loop response of the system and determine the system static map local gradient in an attempt to evaluate the feasibility of extremum-seeking approach of closed-loop control.

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“…6 Feedback control of aerodynamic flow separation is a formidable challenge due to the nonlinear system dynamics and the lack of a closed-form model that describes these dynamics. These difficulties have motivated the use of adaptive control approaches.…”

Section: Introductionmentioning

confidence: 99%

Development of an Improved Performance Function for the Control of Flow Separation

Reese

Alvi

Collins

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Feedback control of aerodynamic flow separation is a formidable challenge due to the nonlinear system dynamics and the lack of a closed-form model that describes these dynamics. Recently, adaptive control approaches have been employed to meet this challenge. However, the performance and robustness achieved using these algorithms is limited due to the fact that the sensors in flow control systems are not used to estimate lift and drag, the quantities of interest. This paper derives a physics-based performance function that is based on estimating the ratio lift/drag and correlates closely with simulated and experimental aerodynamic performance. The developments are based on a NACA 0025 airfoil at a range of near-transitional Reynolds numbers and a range of pre-stall and post-stall angles of attack. The simulation and experimental results consider the use of four pressure measurements. Both the simulated and experimental results indicate that the resulting performance function has properties favorable to closed-loop control. The performance function developed here may be applied to any feedback control framework.

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Adaptive Feedback Control of Flow Separation

Cited by 34 publications

References 11 publications

Transient dynamics of the flow around a NACA 0015 airfoil using fluidic vortex generators

Transient dynamics of the flow around a NACA 0015 airfoil using fluidic vortex generators

Experimental Detection and Pulsed Jets Control of Turbulent Boundary Layer Separation

Development of an Improved Performance Function for the Control of Flow Separation

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