Flow Control Using Moving Surface at the Leading Edge of Aerofoil

Faisal, Kh. Md.; Salam, Md. Abdus; Ali, Mohammad; Sarkar, Md. Samad; Safa, Wasiul; Sharah, Nahreen

doi:10.3329/jme.v47i1.35420

Cited by 5 publications

(3 citation statements)

References 9 publications

(10 reference statements)

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“…Following this, the numerical analysis by Huda et al (2015) incorporated a leading-edge rotating cylinder onto the NACA 0010 aerofoil at a rotational speed of 30, 60, 90, and 120 RPM, thereby generating a surprising improvement in the maximum lift of 145% in comparison with the unmodified NACA 0010 aerofoil model. Similarly, Faisal et al (2017) have undertaken experimental and numerical analyses both by applying the leading-edge rotating cylinder onto NACA 0018. However, the scholars did not record the pre-and post-aerodynamic characteristics of the modified aerofoil.…”

Section: Introductionmentioning

confidence: 99%

Comparative Computational Study of Double Rotating Cylinder Embedded on Selig S1223 Aerofoil and Flat Plate for High Altitude Platform

Ali¹,

Rafie²,

Hamid³

et al. 2022

JST

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The high-altitude platform was built as an alternative approach to address the weakness of the terrestrial and satellite communication networks. It can be an aircraft or balloon positioned 20 to 50 km above the earth’s atmosphere. The use of the Magnus effect was not noticeable in the production of the high-altitude platform, while past research study has denoted its aerodynamic performance in generating greater lift and stall angle delay, which would be beneficial in creating such a flying device. This research delineates the proposed designs using the computational fluid dynamics approach utilizing ANSYS WORKBENCH 2019 software. The embedment of the rotating cylinder onto the design would best portray the use of the Magnus effect in generating higher lift coefficients with probable delay in stall angle. Hereby, the design of embedding rotating cylinder onto Selig S1223 aerofoil and the flat plate is proposed to test their aerodynamic performances for high altitude platform purposes. Here, Fluent fluid flow analysis was simulated for 500 RPM and 1000 RPM momentum injection with free stream velocities from 5 m/s to 30 m/s for different angles of attack of 0 to 20 degrees. The analysis has resulted in a greater impact on its lift coefficient and stall angle delay of about 39% and 53% enhancement for modified aerofoil while showing 128% and 204% betterment for modified flat plate than their respective unmodified model. Therefore, it is perceived that the CyFlaP has better stability yet is simplistic in a design suitable for HAP application.

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Section: Introductionmentioning

confidence: 99%

Comparative Computational Study of Double Rotating Cylinder Embedded on Selig S1223 Aerofoil and Flat Plate for High Altitude Platform

Ali¹,

Rafie²,

Hamid³

et al. 2022

JST

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“…But their research was restricted to only two velocity ratios: 0 and 2 respectively. In 2017, Faisal et al conducted an investigation on controlling the flow using a rotating cylinder at the leading edge of NACA 0018 aerofoil [31]. Their study was limited to only symmetric aerofoil.…”

Section: Introductionmentioning

confidence: 99%

Moving Surface Boundary Layer Control Analysis and the Influence of the Magnus Effect on an Aerofoil with a Leading-Edge Rotating Cylinder

Salam¹,

Hai²,

Ali³

et al. 2019

Preprint

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A number of experimental and numerical studies point out that incorporating a rotating cylinder can superiorly enhance the aerofoil performance, especially for higher velocity ratios. Yet, there have been less or no studies exploring the effects of lower velocity ratio at a higher Reynolds number. In the present study, we investigated the effects of Moving Surface Boundary-layer Control (MSBC) at lower velocity ratios (i.e. cylinder tangential velocity to free stream velocity) and higher Reynolds number on a symmetric aerofoil (e.g. NACA 0021) and an asymmetric aerofoil (e.g. NACA 23018). In particular, the aerodynamic performance with and without rotating cylinder at the leading edge of the NACA 0021 and NACA 23018 aerofoil was studied on the wind tunnel installed at Aerodynamics Laboratory. The aerofoil section was tested in the low subsonic wind tunnel, and the lift coefficient and the drag coefficient were studied for different angles of attack. The experiments were conducted for two Reynolds numbers: 200000 and 250000 corresponding to two free stream velocities: 20 m/s and 25 m/s, respectively, for six different angle of attacks (-5°, 0°, 5°, 10°, 15° and 20°). This study demonstrates that the incorporation of a leading edge rotating cylinder results in an increase of lift coefficient at lower angle of attacks (maximum around 33%) and delay in stall angle (from 10° to 15°) relative to the aerofoil without rotating cylinder.

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“…But their investigation was limited to only two velocity ratios -1 and 2. Faisal et al studied experimental and numerical on symmetric NACA 0018 airfoil using a leading-edge rotating cylinder in 2017 [12]. But they did not carry out any analysis on the pre and post stall characteristics of the modified airfoil.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil

Salam¹,

Deshpande²,

Khan³

et al. 2019

EJERS

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The moving surface boundary control (MSBC) has been a Centre stage study for last 2-3 decades. The preliminary aim of the study was to ascertain whether the concept can improve the airfoil characteristics. Number of experimental and numerical studies pointed out that the MSBC can superiorly enhance the airfoil performance albeit for higher velocity ratios (i.e. cylinder tangential velocity to free stream velocity). Although abundant research has been undertaken in this area on different airfoil performances but no attempt was seen to study effect of MSBC on NACA0021 airfoil for and also effects of lower velocity ratios. Thus, present paper focusses on numerical study of modified NACA 0021 airfoil with leading edge rotating cylinder for velocity ratios (i.e.) between 1 to 1.78 at different angles of attack. The numerical study indicates that the modified airfoil possess better aerodynamic performance than the base airfoil even at lower velocity ratios (i.e. for velocity ratios 0.356 and beyond). The study also focusses on reason for improvement in aerodynamic performance by close look at various parameters.

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Flow Control Using Moving Surface at the Leading Edge of Aerofoil

Cited by 5 publications

References 9 publications

Comparative Computational Study of Double Rotating Cylinder Embedded on Selig S1223 Aerofoil and Flat Plate for High Altitude Platform

Comparative Computational Study of Double Rotating Cylinder Embedded on Selig S1223 Aerofoil and Flat Plate for High Altitude Platform

Moving Surface Boundary Layer Control Analysis and the Influence of the Magnus Effect on an Aerofoil with a Leading-Edge Rotating Cylinder

Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil

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