Numerical Study of Blowing and Suction Control Mechanism on NACA0012 Airfoil

2004 ◽  
Vol 41 (5) ◽  
pp. 1005-1013 ◽  
Author(s):  
L. Huang ◽  
P. G. Huang ◽  
R. P. LeBeau ◽  
T. Hauser
Keyword(s):  
Control Mechanism ◽  
Numerical Study ◽  
Naca0012 Airfoil ◽  
Suction Control

Numerical Study of Camber Morphing in NACA0012 Airfoil

2020 ◽  
Author(s):  
Karthick Dhileep ◽  
D. Kumar ◽  
Santanu Ghosh ◽  
Shaikh Faruque Ali ◽  
Arockiarajan A
Keyword(s):  
Numerical Study ◽  
Naca0012 Airfoil

Numerical study of passive and active flow separation control over a NACA0012 airfoil

2008 ◽  
Vol 37 (8) ◽  
pp. 975-992 ◽  
Author(s):  
Hua Shan ◽  
Li Jiang ◽  
Chaoqun Liu ◽  
Michael Love ◽  
Brant Maines
Keyword(s):  
Flow Separation ◽  
Numerical Study ◽  
Separation Control ◽  
Flow Separation Control ◽  
Naca0012 Airfoil ◽  
Active Flow

NUMERICAL STUDY OF CONTROL OF FLOW SEPARATION OVER A RAMP WITH NANOSECOND PLASMA ACTUATOR

2016 ◽  
Vol 42 ◽  
pp. 1660151
Author(s):  
J. G. ZHENG ◽  
B. C. KHOO ◽  
Y. D. CUI ◽  
Z. J. ZHAO ◽  
J. LI
Keyword(s):  
Flow Separation ◽  
Control Mechanism ◽  
Numerical Study ◽  
Active Flow Control ◽  
Ambient Air ◽  
High Voltage Pulse ◽  
External Flow ◽  
Characterization Study ◽  
Active Flow ◽  
Residual Heat

The nanosecond plasma discharge actuator driven by high voltage pulse with typical rise and decay time of several to tens of nanoseconds is emerging as a promising active flow control means in recent years and is being studied intensively. The characterization study reveals that the discharge induced shock wave propagates through ambient air and introduces highly transient perturbation to the flow. On the other hand, the residual heat remaining in the discharge volume may trigger the instability of external flow. In this study, this type of actuator is used to suppress flow separation over a ramp model. Numerical simulation is carried out to investigate the interaction of the discharge induced disturbance with the external flow. It is found that the flow separation region over the ramp can be reduced significantly. Our work may provide some insights into the understanding of the control mechanism of nanosecond pulse actuator.

Numerical study on the control mechanism of cloud cavitation by obstacles

2010 ◽  
Vol 22 (S1) ◽  
pp. 750-755 ◽  
Author(s):  
Wei-guo Zhao ◽  
Ling-xin Zhang ◽  
Xue-ming Shao ◽  
Jian Deng
Keyword(s):  
Control Mechanism ◽  
Numerical Study ◽  
Cloud Cavitation

Numerical Study of NACA 0012 Aeroacoustics Response for Normal and Icing Conditions

2018 ◽  
Vol 875 ◽  
pp. 89-93
Author(s):  
Edison H. Caicedo ◽  
Muhammad S. Virk
Keyword(s):  
Numerical Study ◽  
Turbulence Models ◽  
Aerodynamic Characteristics ◽  
Sound Level ◽  
Detached Eddy Simulation ◽  
Blade Profile ◽  
Eddy Simulation ◽  
Naca0012 Airfoil ◽  
Layer Flow ◽  
Naca 0012

This paper describes a multiphase computational fluid dynamics (CFD) based numerical study about aeroacoustics response of NACA0012 airfoil for both normal and icing conditions. Three different turbulence models (RANS, DES & LES) are tested where Detached Eddy simulation (DES) turbulence modelling approach is found suitable for this case study. Aeroacoustics numerical results for clean NACA 0012 are compared with the experimental data obtained from NASA report 1218 [1], where a good agreement is found. An extended CFD study is carried out for iced NACA 0012 airfoil, where results show more boundary layer flow separation in case of iced blade profile that leads to a change in the aerodynamic characteristics of the blade profile and increase in sound level for iced airfoil as compared to the clean NACA0012 airfoil.

scholarly journals Numerical study of the application of capillary barrier systems for prevention of rainfall-induced slope instabilities

2020 ◽  
Vol 195 ◽  
pp. 01027
Author(s):  
Riccardo Scarfone ◽  
Simon J. Wheeler ◽  
Colin C. Smith
Keyword(s):  
Numerical Study ◽  
Slope Instability ◽  
Degree Of Saturation ◽  
Atmospheric Conditions ◽  
Capillary Barrier ◽  
Fine Grained ◽  
Suction Control ◽  
Fine Grained Soil ◽  
Improved Stability ◽  
Slope Instabilities

Slope instability is often caused by decreases in suction due to heavy and prolonged rainfall. In this study, the application of capillary barrier systems (CBSs) for suction control and slope stabilization purposes (i.e. reducing the risk of rainfall-induced slope instabilities) is analysed, due to their capacity to limit the percolation of water into the underlying soil. The behaviour of two slopes was studied numerically: a bare slope made of fine-grained soil and the same slope covered by a capillary barrier system. The time evolution of suction in the slopes subjected to realistic atmospheric conditions was studied by performing numerical finite element analyses with Code_Bright. In particular, multi-phase multi-physics thermo-hydraulic analyses were performed, modelling the soil-atmosphere interaction over periods of many years. Suction and degree of saturation distributions obtained from these analyses were then exported to the software LimitState GEO, which was used to perform limit analysis to assess the stability of the slopes. The CBS was able to limit the percolation of water into the slope and was shown to be effective in increasing the minimum values of suction attained in the underlying ground, resulting in improved stability of the slope.

A Numerical Study of the Airfoil Aerodynamic Characteristics with Porous Surface

2014 ◽  
Vol 978 ◽  
pp. 123-130
Author(s):  
Xiao Jun Xiang ◽  
Jun Li Yang
Keyword(s):  
Shock Wave ◽  
Flow Control ◽  
Flow Separation ◽  
Numerical Study ◽  
Aerodynamic Characteristics ◽  
Porous Surface ◽  
Effective Control ◽  
Passive Flow Control ◽  
Naca0012 Airfoil ◽  
Passive Flow

Numerical simulations have been done to investigate the effect of passive flow control on the flow separation and the strength of the shock wave of the NACA0012 airfoil with two types of the porous surface. It has also been discussed that which region the porous surface applied to will make better effect on the flow control. The results show that the B type of the porous surface, which has empty bottom, has effective control on the flow separation if applied to the region near behind the separation point, while the A type of the porous surface is useless. And both A and B porous surface have effect on the decreasing of the strength of the normal shock wave strength when the porosities have been applied to the region across the shock wave. And compared with A type porous surface, the effect of the control is better if B type porous surface is applied. The result has been concluded that the aerodynamic characteristics of the airfoil can be improved with B type of the porous surface. And the B type is worth to be used.

Influence of Tangential Synthetic Jet Location on Flow Control

2016 ◽  
Author(s):  
A. Abdi ◽  
M. Tadjfar ◽  
M. Bayati
Keyword(s):  
Numerical Study ◽  
Cross Flow ◽  
Suction Side ◽  
Aerodynamic Characteristics ◽  
Synthetic Jet ◽  
Base Flow ◽  
Navier Stokes ◽  
Separation Control ◽  
Blowing Ratio ◽  
Naca0012 Airfoil

A numerical study of separation control has been made to investigate aerodynamic characteristics of a NACA0012 airfoil with a tangential synthetic jet. Simulations are carried out at the chord Reynolds number of Re=1,000,000. The present approach relies on solving the Unsteady Reynolds-Averaged Navier–Stokes (URANS) equations. The turbulence model used in the present computation is the K-ω SST equations. All computations are performed with a finite volume based code. We have varied the synthetic jet position on the suction side of the airfoil at various locations from 4% of the chord all the way up to 60% of the airfoil chord. The jet oscillating frequency of fj = 15 Hz, (which corresponds to the non-dimensional oscillating frequency of Fjet+ = 1 when the jet is placed at the 12% chord location), and the blowing ratio of Vj/U∞ = 2 are used during the control cycle. All the cases considered here are for the airfoil at the constant angle of attack of α = 19°, where the airfoil stalls in the uncontrolled base flow. We found that stall characteristics are significantly improved by controlling the formation of separation vortices in the flow. The airfoil lift is more than doubled by placing the tangential synthetic jet anywhere between 20% chord to 50% chord location. This corresponds to a 25% improvement over the best cases reported by Chapin and Benard (2015) for a cross flow synthetic jet.

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