Effects of low and high frequency actuation on aerodynamic performance of a supercritical airfoil

Abdolahipour, Soheila

doi:10.3389/fmech.2023.1290074

Cited by 9 publications

(7 citation statements)

References 38 publications

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“…Also, figure 19 shows vorticity cloud maps that have been calculated using the group-averaged turbulent fluctuation velocity, with 0°, 10°, and 15°angles of attack. In this process, the literature [52] has been referred to and the Q-criterion has been used to map the clouds. Furthermore, figures 18 and 19 show that the groupaveraged turbulent fluctuation velocity, as calculated by using the PAFV turbulence model, has a stronger anisotropy.…”

Section: Comparison and Analysis Of Calculated Resultsmentioning

confidence: 99%

Implementation of a PAFV turbulence model for airfoil flow simulation on OpenFOAM

Yan,

Sun,

Sun

et al. 2024

Phys. Scr.

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To further develop a more effective turbulence model and to improve the calculation accuracy of the flow around airfoil, a new PAFV turbulence model has here been constructed by using a deformation rate tensor and the grouping of an average fluctuation velocity. To evaluate the applicability of the PAFV turbulence model, the numerical calculations of flow around the airfoil have here been implemented, which was based on the OpenFOAM calculation platform. On the basis of grid independence research, the model was used to calculate the low-speed flow-around problem for the plano-convex airfoil NACA4412 and the symmetric airfoil NACA0012. It was also compared with the S-A (Spalart-Allmaras) and SST (Shear Stress Transport) k-ω turbulence models. Firstly, the maximum lift angle-of-attack case of the NACA4412 airfoil was calculated. Thereafter, numerical calculations were performed for the flow around the airfoil in the multi-angle-of-attack case of NACA0012 airfoil. The results showed that the NACA4412 airfoil had an obviously separated vortex at the trailing edge of the airfoil at the maximum lift angle of attack. Also, there was a certain velocity loss downstream of the trailing edge, as was calculated by all three models. However, the results of the PAFV turbulence model were found to be better than those of the S-A and SST turbulence models. The three turbulence models showed comparable accuracies for the calculations of the surface pressure coefficients of the NACA0012 airfoil. However, the S-A and SST k-ω turbulence models were slightly better for the calculations of the mean velocity profiles of the NACA0012 airfoil. Also, the PAFV turbulence model was more accurate for the calculations of the lift and drag coefficients. In conclusion, the PAFV model can make effective predictions for the airfoil low-speed flow around the problem at hand, which in turn preliminarily verifies the applicability of this turbulence model for the low-speed flow around airfoil problems.

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Section: Comparison and Analysis Of Calculated Resultsmentioning

confidence: 99%

Implementation of a PAFV turbulence model for airfoil flow simulation on OpenFOAM

Yan,

Sun,

Sun

et al. 2024

Phys. Scr.

View full text Add to dashboard Cite

show abstract

“…Studies describing the fluid flow around other geometries like airfoils have also been conducted (Bajalan et al, 2011;Mirzaei et al, 2012;Rangan and Santanu Ghosh, 2022;Abdolahipour, 2023). Another aspect of fluid-solid interactions is flow control around bluff bodies.…”

Section: Gnatowska Et Al (2020)mentioning

confidence: 99%

Analysis of the wake mechanism in external flow around tandem bluff bodies with different aspect ratios

Abbasi,

Ehsan,

Rahman

et al. 2024

Front. Mech. Eng.

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The interaction mechanism of external flow with two inline rectangular cylinders having different aspect ratios under the impact of gap spacing (G) is the subject of this research. The gap spacing between the cylinders was varied from 0.25 to 20 times their size. Both cylinders were vertically mounted, with the first having a higher aspect ratio than the second. The results revealed five distinct flow patterns under the influence of G: single slender body, shear layer reattachment, intermittent shedding, binary vortex street, and single-row vortex street. The mean pressure on both cylinders was found to vary due to changes in flow patterns. Both cylinders bore the same shedding frequency but had different pressure variations. The second cylinder placed in the wake of first experienced negative average drag force for some spacing values, while the first cylinder had positive average drag values for all chosen G. Due to the change in flow pattern from shear layer reattachment to intermittent shedding flow, the negative drag force on the second cylinder jumped to a positive drag. It was also observed that the rms values of drag and lift force coefficients, as well as their amplitudes for the second cylinder, were mostly higher than corresponding values for the first cylinder at all selected G. This study revealed that G = 4 and 8 are the critical gap spacing values due to sudden changes in fluid force parameters.

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“…They have been proposed as a potential technique to prevent water droplet icing on aircraft wings in areas not covered by the anti-ice system (Taeibi Rahni et al, 2022). Furthermore, fluidic actuators can inject momentum into low momentum areas, providing significant benefits (Abdolahipour, 2023). Abdolhaipour et al have introduced a novel type of pulsed jet, known as a modulated pulse jet (Abdolahipour et al, 2021;Abdolahipour et al, 2022a;Abdolahipour et al, 2022b), and experimentally applied it as a hybrid active control method on the flap of a high-lift device with a supercritical airfoil section to improve the wing's aerodynamic performance.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic design of a double slotted morphed flap airfoil– a numerical study

Shahrokhi,

Taeibi Rahni,

Akbari

2024

Front. Mech. Eng.

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Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reynolds numbers of 4.7×106. To conduct the simulation, ANSYS FLUENT flow solver and POINTWISE grid generator were utilized. The morphing technique employed involved adjusting both flap mean camber and flap slots, ensuring minimal flow interferences. By discretizing the flap mean camber line, various flap geometries were achieved.Results and Discussions:The findings reveal a significant enhancement in the airfoil’s aerodynamic efficiency attributed to the implementation of the new flap design. The study shows that utilizing double-slotted morphing in the NACA 4412 airfoil at a 30° flap deflection angle increased the lift coefficient by 82% compared to the un-morphed state. A comparison of lift coefficients between this research and the NACA 4412 split flap at a 60° deflection angle indicates that the double-slotted morphing in the NACA 4412 airfoil at a smaller deflection angle of 30° results in a 14% higher maximum lift coefficient.

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Effects of low and high frequency actuation on aerodynamic performance of a supercritical airfoil

Cited by 9 publications

References 38 publications

Implementation of a PAFV turbulence model for airfoil flow simulation on OpenFOAM

Implementation of a PAFV turbulence model for airfoil flow simulation on OpenFOAM

Analysis of the wake mechanism in external flow around tandem bluff bodies with different aspect ratios

Aerodynamic design of a double slotted morphed flap airfoil– a numerical study

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