Active Flow Control for an Outer Wing Model of a Take-off Transport Aircraft Configuration - A Numerical Study

2014 ◽  
Author(s):  
Vlad Ciobaca ◽  
Jochen W. Wild
Keyword(s):  
Flow Control ◽  
Numerical Study ◽  
Active Flow Control ◽  
Transport Aircraft ◽  
Wing Model ◽  
Active Flow

scholarly journals Active Flow Control Systems Architectures for Civil Transport Aircraft

2010 ◽  
Vol 47 (6) ◽  
pp. 1966-1981 ◽  
Author(s):  
M. Jabbal ◽  
S. C. Liddle ◽  
W. J. Crowther
Keyword(s):  
Flow Control ◽  
Control Systems ◽  
Active Flow Control ◽  
Transport Aircraft ◽  
Systems Architectures ◽  
Active Flow

scholarly journals Numerical study on the steady suction active flow control of hydrofoil in the profile of the blended-wing-body underwater glider

2021 ◽  
Vol 39 (4) ◽  
pp. 801-809
Author(s):  
Xiaoxu Du ◽  
Lianying Zhang
Keyword(s):  
Flow Control ◽  
Numerical Study ◽  
Active Flow Control ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Hydrodynamic Performance ◽  
Flow State ◽  
Underwater Glider ◽  
Blended Wing Body ◽  
Active Flow

The hydrodynamic performance of the blended-wing-body underwater glider can be improved by opening a hole on the surface and applying the steady suction active flow control. In order to explore the influence law and mechanism of the steady suction active flow control on the lift and drag performance of the hydrofoil, which is the profile of the blended-wing-body underwater glider, based on the computational fluid dynamics (CFD) method and SST k-ω turbulence model, the steady suction active flow control of hydrofoil under different conditions is studied, which include three suction factors: suction angle, suction position and suction ratio, as well as three different flow states: no stall, critical stall and over stall. Then the influence mechanism in over stall flow state is further analyzed. The results show that the flow separation state of NACA0015 hydrofoil can be effectively restrained and the flow field distribution around it can be improved by a reasonable steady suction, so as to the lift-drag performance of NACA0015 hydrofoil is improved. The effect of increasing lift and reducing drag of steady suction is best at 90° suction angle and symmetrical about 90° suction angle, and it is better when the steady suction position is closer to the leading edge of the hydrofoil. In addition, with the increase of the suction ratio, the influence of steady suction on the lift coefficient and drag coefficient of hydrofoil is greater.

Wind Tunnel Experiments with Active Flow Control for an Outer Wing Model

2015 ◽  
Author(s):  
Vlad Ciobaca ◽  
Jochen Wild ◽  
Matthias Bauer ◽  
Thomas Grund ◽  
Claus-Philipp Huehne ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Flow Control ◽  
Active Flow Control ◽  
Wind Tunnel Experiments ◽  
Wing Model ◽  
Active Flow

Numerical Study of Active Flow Control for a Transitional Highly Loaded Low-Pressure Turbine

2006 ◽  
Vol 128 (5) ◽  
pp. 956-967 ◽  
Author(s):  
Donald P. Rizzetta ◽  
Miguel R. Visbal
Keyword(s):  
Flow Control ◽  
Numerical Study ◽  
Active Flow Control ◽  
Low Pressure ◽  
Transitional Flow ◽  
Suction Surface ◽  
Low Pressure Turbine ◽  
Baseline Case ◽  
Active Flow ◽  
Highly Loaded

Active control was simulated numerically for the subsonic flow through a highly loaded low-pressure turbine. The configuration approximated cascade experiments that were conducted to investigate a reduction in turbine stage blade count, which can decrease both weight and mechanical complexity. At a nominal Reynolds number of 25,000 based upon axial chord and inlet conditions, massive separation occurred on the suction surface of each blade due to uncovered turning. Vortex generating jets were then used to help mitigate separation, thereby reducing wake losses. Computations were performed using both steady blowing and pulsed mass injection to study the effects of active flow control on the transitional flow occurring in the aft-blade and near-wake regions. The numerical method utilized a centered compact finite-difference scheme to represent spatial derivatives, that was used in conjunction with a low-pass Pade-type nondispersive filter operator to maintain stability. An implicit approximately factored time-marching algorithm was employed, and Newton-like subiterations were applied to achieve second-order temporal accuracy. Calculations were carried out on a massively parallel computing platform, using domain decomposition to distribute subzones on individual processors. A high-order overset grid approach preserved spatial accuracy in locally refined embedded regions. Features of the flowfields are described, and simulations are compared with each other, with available experimental data, and with a previously obtained baseline case for the noncontrolled flow. It was found that active flow control was able to maintain attached flow over an additional distance of 19–21% of the blade chord, relative to the baseline case, which resulted in a reduction of the wake total pressure loss coefficient of 53–56%.

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