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

Mehraban, AA; Djavareshkian, Mohammad Hassan

doi:10.1177/0954406220975422

Cited by 4 publications

(3 citation statements)

References 48 publications

(66 reference statements)

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“…12 Consequently, achievements such as diminishing the suction of flow in the peak zones, early occurrence of the transition, and even sub-harmonic behaviors have been reported. 13 Similar analyzes of the influence of the leading-edge protuberances on aerodynamic performance and flow characteristics at pre-and post-stall angles by other researchers with numerical simulations, 6,14-18 experimental approaches, 5,[19][20][21][22][23][24][25] or both methods, [26][27][28][29] can be found. A common feature of previous studies, especially studies that used both experimental and numerical simulations, is performance decline and improvement at pre-and post-stall angles, respectively.…”

Section: Introductionmentioning

confidence: 94%

Static roughness element effects on protuberance full-span wing at micro aerial vehicle application

Jabbari

Djavareshkian

Esmaeili

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Although the tubercle wings provide good maneuverability at post-stall conditions, the aerodynamic performance at pre-stall angles is threatened by forming a laminar separation bubble at the trough section of the tubercle wing; consequently, the flight endurance and range are reduced. In the present study, the idea of passive flow control is introduced by using the distribution of static roughness elements on a full-span wing with a sinusoidal leading edge. Initially, the effect of roughness element length, height, and its location are studied at a pre-stall angle (16-degree). Their effect on the laminar separation bubble and vortex shedding formed behind the wing are also investigated. The Reynolds number is assumed to be equal to [Formula: see text] which is in the range of critical Reynolds number and matches to the micro aerial vehicles application. An improved hybrid model, improved delay detached eddy simulation IDDES, has been used to model the flow turbulence structure. In the extended transition region at low Reynolds numbers, the roughness bypassed the instability. Consequently, roughening the surface of the aerofoil increased the boundary layer’s flow momentum, making it more resistible to adverse pressure gradients. By suppressing the bubble, the static roughness element led to pre-stall flow control, which saw an increase in lift coefficient, [Formula: see text], and a decrease in drag coefficient, [Formula: see text]. The results have been demonstrated that the aerodynamic performance, [Formula: see text], has been improved approximately 22.7%, 38%, and 45% for [Formula: see text], and [Formula: see text], respectively. The optimal arrangement of static roughness elements could decline the size of the vortices and strengthen the cores associated with them. This claim can be interpreted with the vortex shedding frequency.

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Section: Introductionmentioning

confidence: 94%

Static roughness element effects on protuberance full-span wing at micro aerial vehicle application

Jabbari

Djavareshkian

Esmaeili

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…They also investigated the effect of ground on wings with sinusoidal leading edge in another study, illustrating that the lift coefficient increased close to the ground. 44…”

Section: Introductionmentioning

confidence: 99%

“…They also investigated the effect of ground on wings with sinusoidal leading edge in another study, illustrating that the lift coefficient increased close to the ground. 44 Since wings are highly used to generate aerodynamic forces, their geometry, especially the edges of the wings, should receive significant attention. Previous research on the flight of birds mostly addressed the flight mechanism of birds with simplified wings due to lower computational cost or empirical complexity.…”

Section: Introductionmentioning

confidence: 99%

Unsteady aerodynamics of flapping bionic eagle wings in forward flight: An experimental and numerical study

Azargoon

Djavareshkian

2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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The aerodynamic performance of fabricated eagle wing with the corrugated trailing edge was investigated experimentally and numerically in this study. In this respect, wings were designed by imitating the bionic eagle wing and fabricated using a 3D printer. Tests on the wings were performed in a wind tunnel for different bending deflection angles, flapping frequencies, angles of attack, and forward flight velocities. As the key parameters, lift and thrust forces, lift-to-drag and input power were compared between eagle wing and simplified wing. The results revealed that the eagle wing with the corrugated trailing edge led the lift force to be improved by 14% on average compared to the simplified wing, with the largest improvement of 45%. Further, the thrust force of a eagle wing was greater than that of the simplified wing (up to 21%). Also, the input power of the simplified wing mechanism was greater than that of the eagle wing. Numerical simulations were performed to study flow physics. After validating the numerical results against the experimental results, the lift and thrust force, lift-to-drag, pressure contours and vortex were compared between the eagle and simplified wings. The results of the numerical simulation revealed that lift-to-drag increased with for eagle wing with the corrugated trailing edge of eagle wing. the pressure difference between the upper and lower surfaces of the eagle wing was larger than that of the simplified wing; therefore, the lift force produced by the eagle wing was larger than that of the simplified wing.

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Unsteady characteristic study on the flapping wing with the corrugated trailing edge and slotted wingtip

Azargoon

Djavareshkian

2023

Aerospace Science and Technology

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

Cited by 4 publications

References 48 publications

Static roughness element effects on protuberance full-span wing at micro aerial vehicle application

Static roughness element effects on protuberance full-span wing at micro aerial vehicle application

Unsteady aerodynamics of flapping bionic eagle wings in forward flight: An experimental and numerical study

Unsteady characteristic study on the flapping wing with the corrugated trailing edge and slotted wingtip

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