Development of an experimental setup for analyzing the influence of Magnus effect on the performance of airfoil

Aktharuzzaman,; Sarker, Md. Samad; Safa, Wasiul; Sharah, Nahreen; Salam, Md. Abdus

doi:10.1063/1.5018550

Cited by 2 publications

(2 citation statements)

References 6 publications

(4 reference statements)

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“…The detailed analysis of the increment of C L max and stall angle is presented in the following table: From the Table-1, it is clear that for NACA 0021 aerofoil the computational gain is higher than the experimental gain for all the velocity ratios, except for case of the zero velocity ratio. Noteworthy, the numerical study does not include the effect of fluid-structure interaction (FSI) [36][37][38][39][40][41][42][43][44][45][46][47]. Thereby, the associated vibration is neglected in the numerical results.…”

Section: Resultsmentioning

confidence: 99%

“…This preliminary study indicates the feasibility of practical implementation of leading edge cylinders for thick aerofoil in aviation, wind turbine, and other applications. The use of the above-mentioned modifications to the aerofoil would add further layer of complexity for the structural health monitoring (SHM) system due to the addition of cylinder-driven vibrations [36][37][38][39][40][41][42][43][44][45][46][47].…”

Section: Discussionmentioning

confidence: 99%

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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

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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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Section: Resultsmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%