Aerodynamic Multi-Parameter Optimization of NACA0012 Airfoil Using Suction/Blowing Jet Technique

Farhadi, Asghar; Rad, Ebrahim Goshtasbi; Emdad, Homayoun

doi:10.1007/s13369-016-2259-3

Cited by 7 publications

(4 citation statements)

References 20 publications

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“…Comparison between the pressure coefficient (C p ) with the numerical results of Huang et al[20], Farhadi et al[45] and experimental results of Gregory and O'reilly[46] for Re = 5 × 10 5 (Ma = 0.021) and α = 18°0…”

mentioning

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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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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“…Good agreement was obtained between computational results and mentioned studies. Also, the pressure coefficient (C p ) was compared with the numerical results of Huang et al [7], Farhadi et al [48] and experimental results of Gregory and O'reilly [49] for Re = 5910 5 and a = 18°, as shown in figure 8. As it can Figure 6.…”

Section: Validationmentioning

confidence: 99%

“…Hence, by locating the blowing slot nearer Figure 8. Comparison between the pressure coefficient (Cp) with the numerical results of Huang et al [7], Farhadi et al [48] and experimental results of Gregory and O'reilly [49]. Table 6.…”

Section: Changes Of Lift and Drag Coefficients Based On Jet Anglesmentioning

confidence: 99%

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

et al. 2019

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This study mainly focused on the comparison of the effect of single and simultaneous suction and blowing jets on the aerodynamic performance of an airfoil with/without flap to evaluate the most effective flow control configuration using computational fluid dynamics (CFD) method. Moreover, the effect of applying single and simultaneous jets have been conducted on delaying and controlling the flow separation. The results were obtained using two-dimensional incompressible Unsteady Reynolds-Averaged Navier-Stokes (URANS), and the turbulence was simulated with SST k-x turbulence model. Also, different parameters including two jet locations (L jet), three jet velocity ratios (R jet), three jet angles (h jet) and three flap deflections (d f) were analyzed to find the most effective case of applying flow control jets to delay the boundary layer separation. It was concluded that applying a single suction jet and simultaneous suction and blowing jets on the flapped airfoil was more effective to improve the lift-to-drag ratio (C L /C D) than applying these jets to the without flap case. The maximum value of C L /C D was achieved by single suction jet for the without flap case which was equal to 73.7. The maximum increment of stall angle over the without flap airfoil and flapped airfoil was obtained by applying single suction jet, which increased the stall angle from 14°to 20°and 14°to 16°for the suction angle of-90°a nd suction velocity ratio of 0.15, respectively.

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“…Combined suction and blowing may also be used to control the LSB. 45 In addition, zero-net-mass-flux injection devices have been developed for the same purpose, 46 but mass injection into the bubble may be more effective, causing a mass imbalance, and affecting also the shear layer entrainment characteristics. 47 It is noteworthy that the LSB formed over standard (or baseline) wing surfaces usually spreads out along the spanwise direction.…”

Section: Introductionmentioning

confidence: 99%

Combined passive and active flow control for fixed-wing micro air vehicles

Esmaeili,

Sousa

2023

International Journal of Micro Air Vehicles

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This study presents the design, implementation, and assessment of a combined passive and active flow control technique with the aim of increasing the aerodynamic performance of fixed-wing Micro Air Vehicles (MAVs). Power consumption restrictions in MAVs support the choice of passive flow control solutions such as the use of a modified (tubercled) wing leading edge. This strategy successfully allows to delay and mitigate aerodynamic stall but detrimental effects are found at pre-stall operating conditions. In order to retrieve the lift-generation capabilities of the baseline wing at pre-stall, a subsidiary active flow control method making use of air blowing was designed and installed in the modified wing. Guidance to the selection of optimum settings was provided by experimental and computational analyses. The resulting hybrid flow control system demonstrated its effectiveness, thus producing generalized lift enhancements irrespectively of the attitude of the wing.

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Aerodynamic Multi-Parameter Optimization of NACA0012 Airfoil Using Suction/Blowing Jet Technique

Cited by 7 publications

References 20 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

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

Combined passive and active flow control for fixed-wing micro air vehicles

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