Surface Flow Control

2010 ◽  
pp. 247-260
Author(s):  
Manabu Iguchi ◽  
Olusegun J. Ilegbusi
Keyword(s):  
Flow Control ◽  
Surface Flow

Aerodynamic Flow Separation Control of Bridge Deck Sections Using Plasma Actuators

2015 ◽  
Author(s):  
Kazutoshi Matsuda ◽  
Kusuo Kato
Keyword(s):  
Flow Control ◽  
Bridge Deck ◽  
Surface Flow ◽  
Bridge Girders ◽  
Plasma Actuators ◽  
Separation Control ◽  
Wind Tunnel Experiments ◽  
Dbd Plasma ◽  
New Approach ◽  
Flow Separation Control

In order to suppress wind-induced vibrations of bridge girders, two general methods are applied: aerodynamic and mechanical countermeasures. In this study, a new approach to suppress wind-induced vibrations, “a dielectric barrier discharge (DBD) plasma actuator”, was investigated through wind tunnel experiments to determine its potential as a device for flow control around bridge deck sections. This approach is already in use in other fields, such as in the fluid dynamics flow control for separation control in wing surface flow. In this study, it was found that there is a possibility that DBD plasma actuators could be used in the future as the devices for suppressing wind-induced vibrations of bridge girders.

Progress in Hypersonic Inlet Flow Controls by Magnetohydrodynamic

2015 ◽  
Vol 730 ◽  
pp. 311-315
Author(s):  
Shuai Zhang ◽  
Guang Hong ◽  
Dong Yu Zhang ◽  
Fu Qianag Cheng
Keyword(s):  
Flow Control ◽  
Large Scale ◽  
Leading Edge ◽  
Mhd Flow ◽  
Surface Flow ◽  
Near Surface ◽  
Hypersonic Inlet ◽  
Boundary Layer Interaction ◽  
Large Scale Flow ◽  
Wave Boundary

The magnetohydrodynamic (MHD) flow control techniques for inlet based on “AJAX” vehicle concept have attracted many researchers’ attention for its potential wide applications in the supersonic flights or the hypersonic ones. In this paper, a preliminary discussion for basic problems that are ionization and magnetic field in the MHD applications is presented. And three major MHD techniques for enhancing inlet aerodynamic performance and operability, which are large scale flow control for enlarging flight scope in Mach/angle-of-attack, near surface flow control for shock wave/boundary layer interaction and leading edge heating-transfer control for enormous thermal load on leading edge of the compression ramp, are briefly explained and reviewed.

Control of Centrifugal Instability in Vortex-Surface Interaction

2015 ◽  
Author(s):  
Vaibhav Kumar ◽  
Nandeesh Hiremath ◽  
Dhwanil Shukla ◽  
Nikolaus Thorrell ◽  
Narayanan Komerath
Keyword(s):  
Flow Control ◽  
Delta Wing ◽  
Active Flow Control ◽  
Angle Of Attack ◽  
Surface Flow ◽  
Near Surface ◽  
Passive Flow Control ◽  
Passive Flow ◽  
Centrifugal Instability ◽  
Active Flow

The interaction of a rotating conical flow with a solid surface generates a centrifugal instability. This occurs in the flow over the wings of certain types of aircraft at high angles of attack. Efforts at our laboratory have detected such structures using near-surface flow diagnostics, and shown that they can be effectively alleviated using passive flow control near the surface. Their alleviation removes the narrowband spectral peak at the nominal location of vertical fins on these aircraft. This paper explores the substitution of active flow control techniques that remain conformal to the surface and are only powered during high angle of attack operation. The occurrence of the phenomenon and its 15-dB alleviation with geometric fences are shown on a rounded-edge 42-degree swept, cropped delta wing at 25 degrees angle of attack. The feasibility and power requirements for the plasma actuator are estimated in this paper. The generation of counter-rotating vortices using a double dielectric barrier discharge actuator is demonstrated.

Effects of surface flow control on fluid flow phenomena and mixing time in a bottom blown bath

1999 ◽  
Vol 30 (4) ◽  
pp. 631-637 ◽  
Author(s):  
Manabu Iguchi ◽  
Ryoji Tsujino ◽  
Kei-Ichi Nakamura ◽  
Mitsuhiro Sano
Keyword(s):  
Fluid Flow ◽  
Flow Control ◽  
Mixing Time ◽  
Surface Flow ◽  
Flow Phenomena

Lift-Generation and Moving-Wall Flow Control Over a Low Aspect Ratio Airfoil

2017 ◽  
Vol 140 (1) ◽  
Author(s):  
Mohammed Amin Boukenkoul ◽  
Feng-Chen Li ◽  
Wen-Li Chen ◽  
Hong-Na Zhang
Keyword(s):  
Aspect Ratio ◽  
Flow Control ◽  
Control Method ◽  
Control Strategies ◽  
Micro Air Vehicles ◽  
Surface Flow ◽  
Speed Ratio ◽  
Moving Wall ◽  
Low Aspect Ratio ◽  
Wall Flow

Despite the big interest in both, micro-air vehicles (MAV) and flow-control strategies, only few studies have investigated the flow-control possibilities over low aspect ratio (LAR) wings flying at low Reynolds numbers (Re). The present study verified the LAR thick airfoils' conformity with the nonlinear lift approximation equation. Then, a moving-wall flow control method was designed and tested over an LAR thick airfoil (0.57 aspect ration (AR), NACA0015 shaped) performing at a chord-based Re of 4 × 104. The moving belt control postponed the stall onset by 25 deg and produced a 103% gain in lift without any saturation signs at a control speed ratio of Ub/U = 6. Particle image velocimetry (PIV) measurements confirmed the effectiveness of the moving-wall control strategy on the upper surface flow reattachment. Moreover, other quantities such as the, vortices, and the swirling strength are investigated.

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