Boundary-Layer Separation Control Using Local Suction and Injection

Atik, Hediye; Walker, David J.

doi:10.2514/6.2005-4937

Cited by 3 publications

(2 citation statements)

References 9 publications

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“…Additionally, the instabilities in the coefficient of lift and drag of the cylinder were reduced drastically. Atik and Walker (2005) investigated the impact of suction and suction/blowing as control mechanisms for separation that occur at the leading edge at high Reynolds number through a series of numerical simulation. They revealed that the suppression impact of a single suction control technique is better than the blow/suction control technique.…”

Section: Introductionmentioning

confidence: 99%

The Suction Control Characteristics of Flow Separation on NACA 23012

et al. 2020

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The enormous loss of momentum leads to stall and adversely affects the aerodynamic performance of aeroplane wings which may lead to a disaster, more importantly, risking the safety of the aeroplane by putting lives of passengers on it in danger. Therefore, this paper focuses on the enhancement of aerodynamic characteristics of NACA 23012 through the mitigation of flow separation and delay of the stall at higher angles of attack by using suction for Reynolds number (Re) = 3.4 x 106 . Considering the different suction features such as suction width, suction position, and suction coefficient, the separation delay capability of a suction control is studied. Also, the lift to drag ratio and the impact of energy consumption variation during the control technique are used for estimating the control effects. The Reynolds Average Navier-Stokes (RANS) equations are employed together with the Menter’s shear stress turbulent model. The result of this study revealed that the jet position just behind the separation point at 0.2 % of the chord length shows an outstanding control outcome on the separation and stall, thereby increasing the lift. The lift to drag ration increased proportionately when the suction jet coefficient was increased. At suction coefficient Cq = 0.00225, a 92.1% drag reduction and 72.7% lift enhancement is observed. Hence, the stall angle is moved beyond 21.5o from an initial angle of 16° and the more energy was saved at a high angle of attack.

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Section: Introductionmentioning

confidence: 99%

The Suction Control Characteristics of Flow Separation on NACA 23012

et al. 2020

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“…Suction control has been studied extensively through experiments and numerical simulation [6][7][8][9][10]. The suction location and suction flow rate are critical parameters in determining the effects of suction.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Suction Control on an Airfoil Using Multi-island Genetic Algorithm

Zhao

Wang

Cao

et al. 2015

Procedia Engineering

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To overcome the disadvantage of large suction requirements, the suction control for drag reduction is optimized. Computational fluid dynamics (CFD), in conjunction with multi-island genetic algorithm (MIGA), is employed to achieve the optimization. An E387 airfoil is employed as the physical model. The suction location and mass flux of a slot are set as the design parameters. The goal is to minimize both the airfoil drag and suction requirement by identifying the optimal suction location on the upper airfoil surface. The effects of different numbers of suction slots were investigated. Results show that the suction control for drag reduction could be optimized using MIGA. For a single-suction slot, the reduction in airfoil drag is up to 8.3%, and the mass flux of a slot reaches the lower limit of the optimization interval. The increase in suction slot number results in a better drag reduction effect, which is accompanied by larger suction requirement and slower convergence. The main reason for airfoil drag reduction is the decrease in the pressure drag.

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Effects of Distributed Suction on an Airfoil at Low Reynolds Number

Wahidi

Bridges

2012

AIAA Journal

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A suction distribution was designed based on Thwaites' criterion of separation. The effectiveness of the designed suction distribution in controlling the size of the laminar separation bubble on a LA2573a airfoil was investigated. The suction distribution was capable of maintaining an unseparated laminar boundary up to the original transition location. The effects of applying different suction rates on the drag were tested. Drag reductions between 14 and 24 % were achieved. The penalty for utilizing suction was estimated by introducing an equivalent suction drag. The analysis showed that the penalty for using suction to reduce the drag was relatively small.

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Boundary-Layer Separation Control Using Local Suction and Injection

Cited by 3 publications

References 9 publications

The Suction Control Characteristics of Flow Separation on NACA 23012

The Suction Control Characteristics of Flow Separation on NACA 23012

Optimization of Suction Control on an Airfoil Using Multi-island Genetic Algorithm

Effects of Distributed Suction on an Airfoil at Low Reynolds Number

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