High-Performance Airfoil with Moving Surface Boundary-Layer Control

Modi, V. J.; Munshi, S. R.; Bandyopadhyay, G.; Yokomizo, T.

doi:10.2514/2.2358

Cited by 32 publications

(5 citation statements)

References 12 publications

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“…V.J. Modi et al's 1998 study found that judicious selection of momentum injection and cylinder surface geometry can improve lift coe cient and stall angle delay in wind tunnel testing, with a momentum injection ratio of UC/U = 4 [4]. Ahmed Z. Al-Garni et al's study found that a leading-edge rotating cylinder increases the sectional lift coe cient and lift-to-drag ratio at low angles of attack, reducing the need for higher angles.…”

Section: Introductionmentioning

confidence: 99%

A Numerical Study on the effect of Rotating Cylinder as Active Flow Control Device for NACA 23015 Airfoil

Ishrak,

Akhter,

Shuvo

2024

Preprint

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Enhancing aerodynamic efficiency through the use of active and passive flow control methods with airfoils is one of the currently researched areas in the aerospace sector. This paper investigates the lift and drag characteristics of a NACA 23015 airfoil at low-velocity ratios using a rotating cylinder as a flow control device. To conduct this study ANSYS Fluent was utilized for simulation. The analysis involved placing the rotating cylinder at locations along the chord length of both the lower surfaces of the airfoil. Additionally, different cylinder diameters were tested for each scenario to assess performance. This study was carried out at Reynolds number Re = 1.5 x 105 corresponding to free stream velocity 15 m/s at seven Angle of Attack (0°,5°,10°,15°,20°,25° and 30°) The findings revealed that incorporating rotating cylinders can significantly enhance the performance of the airfoil. Moreover, it was noted that placing the cylinder at the lower surface improves the aerodynamic performance more compared to that when placed at the leading edge or upper surface at lower angles of attack.

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Section: Introductionmentioning

confidence: 99%

A Numerical Study on the effect of Rotating Cylinder as Active Flow Control Device for NACA 23015 Airfoil

Ishrak,

Akhter,

Shuvo

2024

Preprint

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“…With the advancement in simulation technology, this research has evolved into a more systematic and mature field. Modi [19] investigated the integration of Magnus effect cylinders into symmetrical airfoils of varying configurations, assessing the impact of cylinder embedding at different positions on overall airfoil performance. At high angles of attack (α ≈ 30 • ), the lift coefficient saw an increase of over 200%.…”

Section: Introductionmentioning

confidence: 99%

Enhancing Energy Harvesting Efficiency of Flapping Wings with Leading-Edge Magnus Effect Cylinder

Zhang,

Zhu,

Chen

2024

Biomimetics

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According to the Magnus principle, a rotating cylinder experiences a lateral force perpendicular to the incoming flow direction. This phenomenon can be harnessed to boost the lift of an airfoil by positioning a rotating cylinder at the leading edge. In this study, we simulate flapping-wing motion using the sliding mesh technique in a heaving coordinate system to investigate the energy harvesting capabilities of Magnus effect flapping wings (MEFWs) featuring a leading-edge rotating cylinder. Through analysis of the flow field vortex structure and pressure distribution, we explore how control parameters such as gap width, rotational speed ratio, and phase difference of the leading-edge rotating cylinder impact the energy harvesting characteristics of the flapping wing. The results demonstrate that MEFWs effectively mitigate the formation of leading-edge vortices during wing motion. Consequently, this enhances both lift generation and energy harvesting capability. MEFWs with smaller gap widths are less prone to induce the detachment of leading-edge vortices during motion, ensuring a higher peak lift force and an increase in the energy harvesting efficiency. Moreover, higher rotational speed ratios and phase differences, synchronized with wing motion, can prevent leading-edge vortex generation during wing motion. All three control parameters contribute to enhancing the energy harvesting capability of MEFWs within a certain range. At the examined Reynolds number, the optimal parameter values are determined to be a∗ = 0.0005, R = 3, and ϕ0 = 0°.

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“…In the past decades, scientists have exerted considerable effort to develop flow control techniques. Moreover, various flow control techniques [1] has been used to suppress flow separation such as moving surface control technique [2][3][4] , plasma flow control technique [5][6][7][8] and co-flow jet control technique [9][10][11][12] . Although flow separation on the control surface can be suppressed substantially by these flow control technique, the application of these techniques in engineering are limited because of complicated devices or other reasons.…”

Section: Introductionmentioning

confidence: 99%

Blowing momentum and duty cycle effect on aerodynamic performance of flap by pulsed blowing

Zhou

Wang

et al. 2017

J. Phys.: Conf. Ser.

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Abstract:Control surface, which is often located in the trailing edge of wings, is important in the attitude control of an aircraft. However, the efficiency of the control surface declines severely under the high deflect angle of the control surface because of the flow separation. To improve the efficiency of control surface, this study discusses a flow-control technique aimed at suppressing the flow separation by pulsed blowing at the leading edge of the control surface. Results indicated that flow separation over the control surface can be suppressed by pulsed blowing, and the maximum average lift coefficient of the control surface can be 95% times higher than that of without blowing when average blowing momentum coefficient is 0.03 relative to that of without blowing. Finally, this study shows that the average blowing momentum coefficient and non-dimensional frequency of pulsed blowing are two of the key parameters of the pulsed blowing control technique. Otherwise, duty cycle also has influence on the effect of pulsed blowing. Numerical simulation is used in this study.

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High-Performance Airfoil with Moving Surface Boundary-Layer Control

Cited by 32 publications

References 12 publications

A Numerical Study on the effect of Rotating Cylinder as Active Flow Control Device for NACA 23015 Airfoil

A Numerical Study on the effect of Rotating Cylinder as Active Flow Control Device for NACA 23015 Airfoil

Enhancing Energy Harvesting Efficiency of Flapping Wings with Leading-Edge Magnus Effect Cylinder

Blowing momentum and duty cycle effect on aerodynamic performance of flap by pulsed blowing

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