Issues in active flow control: theory, control, simulation, and experiment

Collis, S. Scott; Joslin, Ronald D.; Seifert, Avi; Theofilis, Vassilios

doi:10.1016/j.paerosci.2004.06.001

Cited by 272 publications

(30 citation statements)

References 152 publications

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“…Some of the most common approaches involve vortex generators [2,3] , miniature trailing edge devices [4] , continuous and oscillatory blowing and suction [5][6][7][8][9] , microjets [10][11][12][13] , and zero-net-mass-flux actuation (e.g., plasma actuators [14] and synthetic jets [15][16][17][18][19][20][21][22][23] ). These methods and their feasibility for full-scale applications have been reviewed and evaluated by numerous authors [24][25][26][27][28][29][30] . The various methods entail different underlying mechanisms to control flow separation and therefore, they inherit specific advantages and disadvantages.…”

Section: Introductionmentioning

confidence: 99%

Parameters Governing Separation Control with Sweeping Jet Actuators

Woszidlo

2011

29th AIAA Applied Aerodynamics Conference

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Section: Introductionmentioning

confidence: 99%

Parameters Governing Separation Control with Sweeping Jet Actuators

Woszidlo

2011

29th AIAA Applied Aerodynamics Conference

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“…Local flow instabilities excited by periodic flow disturbance are an efficient way to alter the mean flow state in comparison to steady flow disturbance. In order to control the mean vortex system effectively, the physical processes involving vortex instabilities need to be understood [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Pulsed Blowing Interacting with a Leading-Edge Vortex

Buzica

Breitsamter

2020

Aerospace

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Manipulation of vortex instabilities for aerodynamic performance increase is of great interest in numerous aeronautical applications. With increasing angle of attack, the leading-edge vortex of a semi-slender delta wing becomes unsteady and eventually collapses, endangering the flight stability. Hence, active flow control by pulsed blowing stabilizes the vortex system, enlarging the flight envelope for such wing configurations. The most beneficial outcome is the reattachment of the separated shear layer during post-stall, contributing to a lift increase of more than 50%. In contrast to high power consuming brute-force actuation, manipulating the flow instabilities offers a more efficient alternative for mean flow field control, which has direct repercussions on the aerodynamic characteristics. However, the flow mechanisms involving jet–vortex and vortex–vortex interactions and the disturbance convection through the flow field are little understood. This paper reports on the unsteady flow field above a generic half delta wing model with a 65 ° sweep angle and its response to periodic blowing. Numerical and experimental results are presented and discussed in a synergistic manner.

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“…Active flow control is a fast growing multidisciplinary science and technology aimed at altering a natural flow state into a more desired state (Lee et al 2003;Collis et al 2004). This technology has been developed in a variety of applications relevant to military and commercial aircraft design.…”

Section: Introductionmentioning

confidence: 99%

Flexible balloon actuators for active flow control

Jiang

Huang

et al. 2012

Microsyst Technol

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A new type of flexible balloon actuator for active flow control is developed. Compared with the existing balloon actuator with a rigid substrate, it possesses total structural flexibility and perfect air-tightness even with internal high pressure gas. Finite element method is used to analyze the mechanical properties of elastic membrane. The maximum deflection of the balloon membrane is calculated to be 1.5 mm. To investigate the control ability of the actuators, numerical simulation is carried out. The results show that the actuators can dramatically alter the flow field within the boundary layer. Flight test shows that the inflated balloon actuators lead to local flow separation. The imbalance of localized pressure on the airfoils induces an extra rolling moment and the rolling angle of the UAV is changed about 30°.

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Issues in active flow control: theory, control, simulation, and experiment

Cited by 272 publications

References 152 publications

Parameters Governing Separation Control with Sweeping Jet Actuators

Parameters Governing Separation Control with Sweeping Jet Actuators

Pulsed Blowing Interacting with a Leading-Edge Vortex

Flexible balloon actuators for active flow control

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