Comparative study of flow separation control using suction and blowing over an airfoil with/without flap

Fatahian, Esmaeel; Nichkoohi, Ali Lohrasbi; Salarian, Hesamoddin; Khaleghinia, Jahanfar

doi:10.1007/s12046-019-1205-y

Cited by 13 publications

(5 citation statements)

References 46 publications

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“…The flow separation control technology has been gradually developed as an important branch of mechanics [6][7][8]. Traditionally, passive [7][8][9] or active [10][11][12][13] devices are used for flow separation control. Passive control devices are those which are not energy consumptive such as trailing-edge flaps [14][15][16] and leadingedge slats [17,18].…”

Section: Introductionmentioning

confidence: 99%

Effects of the hinge position and suction on flow separation and aerodynamic performance of the NACA 0012 airfoil

Fatahian

Nichkoohi

Salarian

et al. 2020

J Braz. Soc. Mech. Sci. Eng.

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In the present study, the effect of hinge position (H) has been numerically investigated to find the appropriate position for improving the aerodynamic performance of the NACA 0012 flapped airfoil. In addition, perpendicular and tangential suctions have been applied to control the flow separation and enhance the aerodynamic performance over the NACA 0012 flapped airfoil at each different hinge positions. The simulations were carried out at a Reynolds number of 5 × 10 5 (Ma = 0.021) based on two-dimensional incompressible unsteady Reynolds-averaged Navier-Stokes calculations to determine the adequate hinge position. The turbulence was modeled using the shear stress transport k-ω turbulence model. The effect of perpendicular suction (θ jet = − 90°) and tangential suction (θ jet = − 30°) was computationally studied over NACA 0012 flapped airfoil for five different hinge positions (H = 0.7c, 0.75c, 0.8c, 0.85c and 0.9c) and a flap deflection (δ f) of 15°. Based on the results, the hinge position significantly affects the aerodynamic performance of the airfoil. The lift coefficient increased clearly as the hinge position moved to the trailing edge of the airfoil. Using perpendicular suction caused to increase the lift coefficient and decrease the drag coefficient. Consequently, the maximum value of the lift-to-drag ratio (C L /C D) for perpendicular and tangential suctions was achieved about 35.8% and 25.1% higher than that of the case without suction at an angle of attack of 12° and H = 0.9c. Also, the effect of perpendicular suction was more considerable compared to the tangential suction. This caused a reduction in the size of the recirculation zone from 0.5 to 0.09 of the airfoil chord length and also transferred it from 1.13 to 1.18 of the airfoil chord length.

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Section: Introductionmentioning

confidence: 99%

Effects of the hinge position and suction on flow separation and aerodynamic performance of the NACA 0012 airfoil

Fatahian

Nichkoohi

Salarian

et al. 2020

J Braz. Soc. Mech. Sci. Eng.

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“…Yk and Yω denote the dissipation of k and ω, respectively. Dω is the crossdiffusion term of ω [36,37].…”

Section: Mathematical Formulationmentioning

confidence: 99%

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Hosseini¹

2021

JMES

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One way to achieve high performance in the gas turbine is to increase the inlet temperature of the turbine. Different cooling techniques have been carried out in order to protect the turbine blades which have been exposed to such high temperatures. Film cooling as an essential cooling method needs to be enhanced to meet the challenging demand. The purpose of the present research is to analyze the film cooling performance over a NACA 0012 gas turbine blade using six different injection holes with and without opening angles, separately through Computational Fluid Dynamics (CFD). 2D Reynolds-Averaged Navier-Stokes (RANS) equations are implemented to consider the heat transfer and flow characteristics by using CFD code Ansys Fluent v16. The flow is considered as steady, turbulent, and incompressible. The RANS equation is solved with the finite-volume method for obtaining solutions. The simulation results revealed that the k-ω SST turbulence model is suitable for simulating the flow characteristics and analyzing the performance of film cooling over the blade. Also, the opening angle has a significant effect on increasing the cooling efficiency for the upper blade surface. The highest value of cooling efficiency is obtained by the injection hole with an opening angle of 15° and height of D. In this configuration, the coolant injected from hole provides better cooling coverage for the entire blade which increases the cooling effectiveness.

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“…Active flow control requires external devices to operate, whereas passive flow control acts independently throughout the whole system. Examples of active flow control are plasma actuators [15], suction and blowing [16,17], and synthetic jets [18,19]. According to Ruisi et al [20], the plasma actuator is capable of reducing the separation length at the flow field with an accurate modulation frequency.…”

Section: Introductionmentioning

confidence: 99%

Improving the Aerodynamic Performance of WIG Aircraft with a Micro-Vortex Generator (MVG) in Low-Speed Condition

Methal,

Talib,

Bakar

et al. 2023

Aerospace

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This present study investigated the potential of passive flow control to reduce induced drag by using a micro-vortex generator (MVG) at a backward-facing step (BFS) location. A wing-in-ground (WIG) craft is a fast watercraft that resembles a dynamically stabilised ship that can move or glide across the surface of water or land. Therefore, the wing of the WIG is designed to glide when in contact with water, which helps to decrease drag and enhance the lift of the overall vehicle. However, the existing design of the hull-fuselage of WIG tends to induce more drag during the flight, especially at a flow downstream of a BFS, which will cause inefficient fuel consumption over the distance travelled. MVG with the ramp type was chosen and tested at various angles (°) and heights (h). The angles (°) tested were 12°, 16°, and 24°, while the heights (h) tested were 0.4 δ, 0.6 δ, and 0.8 δ, where δ refers to the boundary layer height. The model was designed and fabricated using a 3D printer. The 3D model was tested in a subsonic wind tunnel at Re = 6.1 × 104 m−1 to 6.1 × 105 m−1 between 1 and 10 m/s. This study demonstrated that the most effective angle and height of MVG for reducing the drag coefficient were 16° and 0.6 δ, respectively. In comparison to an uncontrolled case, the drag coefficient decreased significantly by 38% compared to the baseline.

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Comparative study of flow separation control using suction and blowing over an airfoil with/without flap

Cited by 13 publications

References 46 publications

Effects of the hinge position and suction on flow separation and aerodynamic performance of the NACA 0012 airfoil

Effects of the hinge position and suction on flow separation and aerodynamic performance of the NACA 0012 airfoil

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Improving the Aerodynamic Performance of WIG Aircraft with a Micro-Vortex Generator (MVG) in Low-Speed Condition

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