Flow control for an airfoil with leading-edge rotation: an experimental study

Ahmed Z. Al-Garni; Abdullah M. Al-Garni; Saad A. Ahmed; Ahmet Z. Sahin

doi:10.2514/2.2673

Flow control for an airfoil with leading-edge rotation: an experimental study

Ahmed Z. Al-Garni, Abdullah M. Al-Garni, Saad A. Ahmed, Ahmet Z. Sahin

King Fahd University of Petroleum & Minerals

Research output: Contribution to journal › Article › peer-review

47 Scopus citations

Abstract

An experimental investigation has been conducted on a two-dimensional NACA 0024 airfoil equipped with a leading-edge rotating cylinder. The airfoil was tested for different values of leading-edge rotations and flap deflection angles. The effects of the angle of attack α, the cylinder surface velocity ratio U_c/U, and the flap deflection angle δ on lift and drag coefficients, the size of the separated flow region, and the stall angle of attack are included. The effect of U_c/U on the boundary-layer growth and turbulence intensity are also shown. Experimental results, for example, showed that the leading-edge rotating cylinder increases the lift coefficient of a NACA 0024 airfoil from 0.85 at U_c/U = 0 to 1.63 at U_c/U = 4 and delays the stall angle of attack by about 160%. Smoke-wire flow visualization results were also used to demonstrate the strong effect of the leading-edge rotating cylinder on the size of the recirculation region.

Original language	English
Pages (from-to)	617-622
Number of pages	6
Journal	Unknown Journal
Volume	37
Issue number	4
DOIs	https://doi.org/10.2514/2.2673
State	Published - 2000

ASJC Scopus subject areas

Aerospace Engineering

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10.2514/2.2673

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title = "Flow control for an airfoil with leading-edge rotation: an experimental study",

abstract = "An experimental investigation has been conducted on a two-dimensional NACA 0024 airfoil equipped with a leading-edge rotating cylinder. The airfoil was tested for different values of leading-edge rotations and flap deflection angles. The effects of the angle of attack α, the cylinder surface velocity ratio Uc/U, and the flap deflection angle δ on lift and drag coefficients, the size of the separated flow region, and the stall angle of attack are included. The effect of Uc/U on the boundary-layer growth and turbulence intensity are also shown. Experimental results, for example, showed that the leading-edge rotating cylinder increases the lift coefficient of a NACA 0024 airfoil from 0.85 at Uc/U = 0 to 1.63 at Uc/U = 4 and delays the stall angle of attack by about 160\%. Smoke-wire flow visualization results were also used to demonstrate the strong effect of the leading-edge rotating cylinder on the size of the recirculation region.",

author = "Al-Garni, \{Ahmed Z.\} and Al-Garni, \{Abdullah M.\} and Ahmed, \{Saad A.\} and Sahin, \{Ahmet Z.\}",

year = "2000",

doi = "10.2514/2.2673",

language = "English",

volume = "37",

pages = "617--622",

journal = "Unknown Journal",

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T1 - Flow control for an airfoil with leading-edge rotation

T2 - an experimental study

AU - Al-Garni, Ahmed Z.

AU - Al-Garni, Abdullah M.

AU - Ahmed, Saad A.

AU - Sahin, Ahmet Z.

PY - 2000

Y1 - 2000

N2 - An experimental investigation has been conducted on a two-dimensional NACA 0024 airfoil equipped with a leading-edge rotating cylinder. The airfoil was tested for different values of leading-edge rotations and flap deflection angles. The effects of the angle of attack α, the cylinder surface velocity ratio Uc/U, and the flap deflection angle δ on lift and drag coefficients, the size of the separated flow region, and the stall angle of attack are included. The effect of Uc/U on the boundary-layer growth and turbulence intensity are also shown. Experimental results, for example, showed that the leading-edge rotating cylinder increases the lift coefficient of a NACA 0024 airfoil from 0.85 at Uc/U = 0 to 1.63 at Uc/U = 4 and delays the stall angle of attack by about 160%. Smoke-wire flow visualization results were also used to demonstrate the strong effect of the leading-edge rotating cylinder on the size of the recirculation region.

AB - An experimental investigation has been conducted on a two-dimensional NACA 0024 airfoil equipped with a leading-edge rotating cylinder. The airfoil was tested for different values of leading-edge rotations and flap deflection angles. The effects of the angle of attack α, the cylinder surface velocity ratio Uc/U, and the flap deflection angle δ on lift and drag coefficients, the size of the separated flow region, and the stall angle of attack are included. The effect of Uc/U on the boundary-layer growth and turbulence intensity are also shown. Experimental results, for example, showed that the leading-edge rotating cylinder increases the lift coefficient of a NACA 0024 airfoil from 0.85 at Uc/U = 0 to 1.63 at Uc/U = 4 and delays the stall angle of attack by about 160%. Smoke-wire flow visualization results were also used to demonstrate the strong effect of the leading-edge rotating cylinder on the size of the recirculation region.

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JF - Unknown Journal

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Flow control for an airfoil with leading-edge rotation: an experimental study

Abstract

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