Effects of smart flap on aerodynamic performance of sinusoidal leading-edge wings at low Reynolds numbers

Mehraban, AA; Djavareshkian, Mohammad Hassan; Sayegh, Y; Feshalami, Behzad Forouzi; Azargoon, Yegane; Zaree, AH; Hassanalian, Mostafa

doi:10.1177/0954410020946903

Cited by 15 publications

(14 citation statements)

References 57 publications

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“…the lowest Reynolds number (Re = 29,000), about 2.95% of the wing is in the wind tunnel boundary layer. 35 This content is less than that of Custodio et al. 46 where the wind tunnel boundary layer covers 4.3 and 7.8% of the model span for the largest and smallest freestream velocities, respectively.…”

Section: Methodsmentioning

confidence: 74%

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Experimental investigation of ground effects on aerodynamics of sinusoidal leading-edge wings

Mehraban

Djavareshkian

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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Sinusoidal leading-edge wings have attracted many considerations since they can delay the stall and enhance the maneuverability. The main contribution of this research study is to experimentally investigate effects of ground on aerodynamic performance of sinusoidal leading-edge wings. To this end, 6 tubercled wings with different amplitudes and wavelengths are fabricated and compared with the baseline wing which has smooth leading-edge. Proposed wings are tested in different distances from the ground in a wind tunnel lab for a wide range of angle of attack from 0° to 36° and low Reynolds number of 45,000. Results indicated that lift coefficient is improved when wings get close to the ground. Furthermore, increment of protuberance amplitude in the vicinity of the ground could efficiently prevent stalling particularly for shorter wavelength.

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Section: Methodsmentioning

confidence: 74%

“…Results showed that the stall angle could be further delayed by adding a smart flap to the trailing-edge of the sinusoidal leading-edge wing. 35…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of ground effects on aerodynamics of sinusoidal leading-edge wings

Mehraban

Djavareshkian

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…In order to understand the concept of nodule, a lot of numerical calculations and experimental studies have been carried out (Corsini et al, 2013;Isaac & Swanson, 2011;Mehraban et al, 2020;Shi et al, 2016).…”

Section: Introductionmentioning

confidence: 99%

An aerodynamic optimization design study on the bio-inspired airfoil with leading-edge tubercles

Chang

et al. 2021

Engineering Applications of Computational Fluid Mechanics

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The aim of the paper is to propose a groundbreaking method for the aerodynamic optimization design of the bioinspired wing with leading-edge tubercles. An emphasis on the optimization design of the spanwise waviness in the leading edge for delaying stall and increasing lift from the aerodynamic performance perspective has been laid in this study. For the conversion of the wavy configuration, the form parameterized approach using F-spline curves has been used to produce more variants of the leading-edge tubercles. Numerical investigations of flow characteristics which are performed using CFD computations have been used to validate the numerical scheme with experimental data. The combination of Non-dominated Sorting Genetic Algorithm II and Response Surface Method based Kriging Model has been adopted as the aerodynamic optimization strategy. As consequence, the three main components of the optimization process are incorporated into the establishment of the aerodynamic optimization design system for the bio-inspired airfoil with leading-edge tubercles. The four optimal airfoils respectively which increases the stall angle as well as the lift have been obtained in contrast to the smooth wing. The optimized bio-inspired design of this kind can be applied to flow-controlled devices for improving the efficiency of a particular operating mechanism.

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“…The spherical TLE controls the leading-edge separation bubble at high angles and improves the C lmax (Aftab and Ahmad, 2017). The improvement in stall delay and the maximum lift coefficient by the sinusoidal leading-edge wing after stall is boosted by a smart flap (Mehraban et al , 2020). The porpoise nose inspired by the marine mammal (Dall’s porpoise) gives an optimum aerodynamic performance at all angles of attack than the base airfoil.…”

Section: Introductionmentioning

confidence: 99%

Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils

Mohamed

Yadav

Güven

2021

AEAT

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Purpose This paper aims to achieve an optimum flow separation control over the airfoil using a passive flow control method by introducing a bio-inspired nose near the leading edge of the National Advisory Committee for Aeronautics (NACA) 4 and 6 series airfoil. In addition, to find the optimised leading edge nose design for NACA 4 and 6 series airfoils for flow separation control. Design/methodology/approach Different bio-inspired noses that are inspired by the cetacean species have been analysed for different NACA 4 and 6 series airfoils. Bio-inspired nose with different nose length, nose depth and nose circle diameter have been analysed on airfoils with different thicknesses, camber and camber locations to understand the aerodynamic flow properties such as vortex formation, flow separation, aerodynamic efficiency and moment. Findings The porpoise nose design that has a leading edge with depth = 2.25% of chord, length = 0.75% of chord and nose diameter = 2% of chord, delays the flow separation and improves the aerodynamic efficiency. Average increments of 5.5% to 6° in the lift values and decrements in parasitic drag (without affecting the pitching moment) for all the NACA 4 and 6 series airfoils were observed irrespective of airfoil geometry such as different thicknesses, camber and camber location. Research limitations/implications The two-dimensional computational analysis is done for different NACA 4 and 6 series airfoils at low subsonic speed. Practical implications This design improves aerodynamic performance and increases the structural strength of the aircraft wing compared to other conventional high lift devices and flow control devices. This universal leading edge flow control device can be adapted to aircraft wings incorporated with any NACA 4 and 6 series airfoil. Social implications The results would be of significant interest in the fields of aircraft design and wind turbine design, lowering the cost of energy and air travel for social benefits. Originality/value Different bio-inspired nose designs that are inspired by the cetacean species have been analysed for NACA 4 and 6 series airfoils and universal optimum nose design (porpoise airfoil) is found for NACA 4 and 6 series airfoils.

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Effects of smart flap on aerodynamic performance of sinusoidal leading-edge wings at low Reynolds numbers

Cited by 15 publications

References 57 publications

Experimental investigation of ground effects on aerodynamics of sinusoidal leading-edge wings

Experimental investigation of ground effects on aerodynamics of sinusoidal leading-edge wings

An aerodynamic optimization design study on the bio-inspired airfoil with leading-edge tubercles

Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils

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