Experimental Study of NACA Symmetric and Camber Airfoils at Low Reynolds Numbers

Garcia, Elifalet; Durgesh, Vibhav; Johari, Hamid

doi:10.2514/6.2017-0771

Cited by 5 publications

(3 citation statements)

References 13 publications

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“…For this purpose, the lift-to-drag ratio of NACA 0009 airfoil from experimental investigations of Sauvageat and Rolin 21 was examined in comparison with the present research in four attack angles of 5°, 7°, 9°, and 11° at the Reynolds number of 40,000, which is presented in Figure 14. Further, the pressure coefficient around the airfoil is compared to the experimental results of Garcia et al 22 in Figure 15. An excellent agreement between the numerical predictions and the experiments was achieved as can be seen from these figures.…”

Section: Numerical Modeling and Solving Methods For Simulationsmentioning

confidence: 99%

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Numerical investigation and parametric study of NACA 0009 airfoil with bumps inspired by mako-shark skin denticles

Arjanki,

Pasandidehfard,

Saberinia

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part C:

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In the current research, a numerical study of 53 airfoils inspired by the surface scales of the mako-shark skin based on NACA0009 airfoil has been performed. The airflow simulations were performed in different angles of attack from 4° to 11° and the validations are presented in two stages compared with two different studies. The diagrams of [Formula: see text] parameter, shear stress, pressure coefficient, and also the contours of velocity and streamlines are reported. The results of the lift, drag, and diagram of lift to drag ratios have been presented and analyzed for different geometries and angles of attack. The results show that by creating bumps’ pattern taken from the shark skin mounted over the suction side of the airfoils the ratio of lift to drag increases. For example up to 28% increment of average of Cl/Cd in the above mentioned range of angles of attack can be obtained utilizing just one bump with 0.7 mm thickness (0.7% of chord length) mounted at 23% of the chord on suction side.

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Section: Numerical Modeling and Solving Methods For Simulationsmentioning

confidence: 99%

“…Pressure coefficient around the NACA0009 airfoil at a 2.5° angle of attack in comparison with experimental data of Garcia et al at Reynolds number of 2 × 10 6 for water flow. 22 …”

Section: Numerical Modeling and Solving Methods For Simulationsmentioning

confidence: 99%

Numerical investigation and parametric study of NACA 0009 airfoil with bumps inspired by mako-shark skin denticles

Arjanki,

Pasandidehfard,

Saberinia

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part C:

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show abstract

“…Lift coefficients were calculated at various angles of attack (0° to 10°), then compared with those obtained in previous research E.N. Garcia et al [21] Shown in Fig. 2 The study conditions under which the current research was conducted were similar to those used in previous studies.…”

Section: Validationmentioning

confidence: 99%

Enhancement of airfoil performance by rotating cylinder

Kadhim

Hamza

2021

QJES

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This study used a NACA 6409 smooth wing section. Its performance is compared to an enhanced design incorporating a revolving cylinder on the upper airfoil surface. The boundary conditions for the present work were Reynolds (105), and the attack angles were (0,2,4,6,8,10,12,14,16). A turbulence model was developed (SST K-), one of the aerodynamics models. This model is well-suited for sensing flow near a wall. The cylinder was evaluated at three positions (25,50,75) percent of the chord's length. The results indicated that position (25 percent C) was optimal, as it resulted in a 24.45 percent increase in lift coefficient at the angle of attack (12). And when the results were compared to those of other studies, they revealed a significant agreement.

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Experimental and computational investigations of the influence of elliptical and square-shaped dimples on performance of NACA 6409 blade profile

Kalugotla,

Dhar Dubey,

Gupta

et al. 2024

J Braz. Soc. Mech. Sci. Eng.

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Experimental Study of NACA Symmetric and Camber Airfoils at Low Reynolds Numbers

Cited by 5 publications

References 13 publications

Numerical investigation and parametric study of NACA 0009 airfoil with bumps inspired by mako-shark skin denticles

Numerical investigation and parametric study of NACA 0009 airfoil with bumps inspired by mako-shark skin denticles

Enhancement of airfoil performance by rotating cylinder

Experimental and computational investigations of the influence of elliptical and square-shaped dimples on performance of NACA 6409 blade profile

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