Flow separation control of NACA-2412 airfoil with bio-inspired nose

Mohamed, Mohamed Arif Raj; Güven, Uğur; Yadav, Rajesh

doi:10.1108/aeat-06-2018-0175

Cited by 8 publications

(2 citation statements)

References 10 publications

(6 reference statements)

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“…The dimensions of this modification can be seen in Figure 2. This dimension was first introduced by Mohamed et al [18]. All dimensions are shown in the form of multiplication of the values of c. The symbol c is the length of the airfoil chord [19].…”

Section: B Modification Of Airfoilsmentioning

confidence: 99%

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Julian

Iskandar

Wahyuni

2023

IJMEIR

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⎯ This research modifies the leading-edge structure of NACA 0015 and NACA 4415 to resemble the nose of a beluga whale. The focus of this modification is to improve the airfoil's aerodynamic performance and investigate the changing fluid flow patterns. Numerical equation used is RANS combined with the k-ε turbulence model. Mesh independence test shows that mesh with 200 elements is the best mesh. Validation results reveal that CFD data can follow the trend of experimental data, especially on the AoA before the stall. There was a significant increase in Cl from NACA 0015 and NACA 4415 at AoA>9°. On the other hand, the modification also had a positive effect by lowering the Cd value. The modification also provides an advantage by increasing the maximum Cl/Cd value. Furthermore, the separation point data shows that the modification can delay the separation of the fluid flow in the airfoil. Modifications can cause an increase in pressure on the lower side and a decrease in pressure on the upper side. Through velocity contours and streamlines, the modifications can reduce the recirculation area. Overall, modifying the leading edge has positive impacts on the NACA 0015 and NACA 4415 airfoils.

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Section: B Modification Of Airfoilsmentioning

confidence: 99%

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Julian

Iskandar

Wahyuni

2023

IJMEIR

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“…The bio-inspired nose designs, which are inspired by the cetacean species nose designs, were analyzed for the subsonic speed and found that the Dall’s Porpoise nose showed the better aerodynamic efficiency at all angles of attack with increase in C l (Raj Mohamed et al , 2019). The optimum bio-inspired (porpoise) nose enhances the aerodynamic efficiency for different NACA 4 and 6 series airfoils; hence, it can be made as a simple and fixed LE device which can be installed easily on the existing aircrafts (Raj Mohamed et al , 2021).…”

Section: Introductionmentioning

confidence: 99%

Bio-inspired optimization of leading edge slat

Mohamed

Reddy

Vishnu

2022

AEAT

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Purpose The high lift devices are effective at high angle of attack to increase the coefficient of lift by increasing the camber. But it affects the low angle of attack aerodynamic performance by increasing the drag. Hence, they have made as a movable device to deploy only at high angles of attack, which increases the design and installation complexities. This study aims to focus on the comparison of aerodynamic efficiency of different conventional leading edge (LE) slat configurations with simple fixed bioinspired slat design. Design/methodology/approach This research analyzes the effect of LE slat on aerodynamic performance of CLARK Y airfoil at low and high angles of attack. Different geometrical parameters such as slat chord, cutoff, gap, width and depth of LE slat have been considered for the analysis. Findings It has been found that the LE slat configuration with slat chord 30% of airfoil chord, forward extension 8% of chord, dip 3% of chord and gap 0.75% of chord gives higher aerodynamic efficiency (Cl/Cd) than other LE slat configurations, but it affects the low angles of attack aerodynamic performance with the deployed condition. Hence, this optimum slat configuration is further modified by closing the gap between LE slat and the main airfoil, which is inspired by the marine mammal’s nose. Thus increases the coefficient of lift at high angles of attack due to better acceleration over the airfoil nose and as well enhances the aerodynamic efficiency at low angles of attack. Research limitations/implications The two-dimensional computational analysis has been done for different LE slat’s geometrical parameters at low subsonic speed. Practical implications This bio-inspired nose design improves aerodynamic performance and increases the structural strength of aircraft wing compared to the conventional LE slat. This fixed design avoids the complex design and installation difficulties of conventional movable slats. Social implications The findings will have significant impact on the fields of aircraft wing and wind turbine designs, which reduces the design and manufacturing complexities. Originality/value Different conventional slat configurations have been analyzed and compared with a simple fixed bioinspired slat nose design at low subsonic speed.

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Flow separation control using the cetacean species nose design

Mohamed

Yadav

2021

European Journal of Mechanics - B/Fluids

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Flow separation control of NACA-2412 airfoil with bio-inspired nose

Cited by 8 publications

References 10 publications

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Bio-inspired optimization of leading edge slat

Flow separation control using the cetacean species nose design

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