Computational study of airfoil performance with the incorporation of a moving surface at the leading edge

Khan, Nafiz Ahmed; Salam, Md. Abdus; Faisal, Kh. Md.; Bhadra, Debanan

doi:10.1063/1.5044326

Cited by 2 publications

(3 citation statements)

References 7 publications

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“…Lift and drag coefficients of symmetric NACA 0021 and asymmetric NACA 23018 aerofoil with a cylinder at their leading edge at three different Reynolds numbers and six different velocity ratios are presented. The computational setup for this study was published in 2018 [35]. Figure-6 represents the computational and experimental analysis of the relationship between the coefficient of lift (C L ) and an angle of attack (AOA) for a base NACA 0021, and a modified NACA 0021 aerofoils.…”

Section: Resultsmentioning

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%

“…Velocity inlet and Pressure outlet is used in the inlet and outlet boundaries, respectively. The wall motion is added to the leading edge cylinder [35].…”

Section: Numerical Approximationmentioning

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

Self Cite

View full text Add to dashboard Cite

show abstract

“…Lift and drag coefficients of symmetric NACA 0021 and asymmetric NACA 23018 aerofoil with a cylinder at their leading edge at three different Reynolds numbers and six different velocity ratios are presented. The computational setup for this study was published in 2018 [40]. Figure-9 represents the computational and experimental analysis of the relationship between the coefficient of lift (C L ) and an angle of attack (AOA) for a base NACA 0021, and a modified NACA 0021 aerofoils.…”

Section: Resultsmentioning

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

Self Cite

View full text Add to dashboard Cite

show abstract

Computational study of airfoil performance with the incorporation of a moving surface at the leading edge

Cited by 2 publications

References 7 publications

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

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

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

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