Behaviour of trailing wing(s) in echelon formation due to wing twist and aspect ratio

Gunasekaran, M.; Mukherjee, Rinku

doi:10.1016/j.ast.2017.01.009

Cited by 12 publications

(1 citation statement)

References 7 publications

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“…The research of the modification of wing configuration to enhance the aerodynamics performance was also conducted by the researcher to investigate the parameter details that affected the winglet performance. It was affected by the wing reference 17) , wing structure 18) , crosssection 19) , aspect ratio 20) , taper ratio 21) , twist angle 22) , sweep angle 23) , span 24) , number of wings 25) and other wing accessories. Considering the literature study, the current study's motivation is to evaluate mutual interaction between taper and Cant angles in aerodynamics performance improvement of Micro UAV.…”

Section: Introduction Overviewmentioning

confidence: 99%

Aerodynamic Performance Enhancement of Wing Body Micro UAV Employing Blended Winglet Configuration

Tjahjana¹,

Yaningsih²,

Imama³

et al. 2021

Evergreen

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The wing-body configuration for Micro Unmanned Aircraft Vehicle (UAV) decides their aerodynamics performance which potentially providing benefits for wing design optimization. This challenge leads to the development of future wing body aircraft. The numerical study, utilizing Computational Fluid Dynamics (CFD), is developed in the current work to analyze blended winglet configuration on their performance. Critical parameters combination of taper ratio together with Cant angle were considered. Six wing designs; with no winglet as a baseline, winglet with constant Cant angle of 60° having 0.3, 0.4, and 0.5 taper ratio values and winglet with a constant taper ratio of 0.3 having 50° and 70° Cant angles values, were investigated to observe the vortex distribution and streamline flow behavior of the wingtips. Besides, their effect on lift and drag coefficients and lift to drag ratios were also investigated. Using Reynolds-Averaged-Navier-Stokes (RANS) equation coupled with kω Shear Stress Transport (SST) turbulent model, the current design founds that the best blended-winglet configuration for Micro UAV was the combination of taper ratio of 0.3 and Cant angle of 50°. It enhances the average lift to drag ratio to 9.84% while reducing the average wingtips vortex to 17% compared to the baseline (with no winglet).

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Section: Introduction Overviewmentioning

confidence: 99%

Aerodynamic Performance Enhancement of Wing Body Micro UAV Employing Blended Winglet Configuration

Tjahjana¹,

Yaningsih²,

Imama³

et al. 2021

Evergreen

View full text Add to dashboard Cite

show abstract

Aerodynamic Characteristics of Finite Rectangular Wings in Formation Flight with Ground Effect

Shirsath,

Mukherjee

2024

Lecture Notes in Mechanical Engineering

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Parametric Study on Formation Flying Effectiveness for a Blended-Wing UAV

Shin

Antoniadis

Tsourdos

2018

J Intell Robot Syst

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This paper investigates aerodynamic performance improvements of formation flight at transonic speeds for a medium size Unmanned Aerial Vehicle (UAV). The metric for assessing the aerodynamic improvement of formation flight is the computed drag. The total drag for each formation configuration is compared with a single UAV, where a final drag reduction percentage is estimated. The evaluation of the aerodynamic performance is conducted by employing an in-house Computational Fluid Dynamics (CFD) solver, grid generation and post processing tools. For critical understanding of the tendency of the formation efficiency depending on main parameters, broad formation configurations are analysed. The parameterisation includes number of aircraft, proximity and formation shape. Full realisation of the benefit predicted would need to be proven in the real world, but there is sufficient confidence to suggest that it exist: the empirical parametric analysis suggests that formation flight can improves aerodynamic performance and formation configuration greatly influence the degree of improvement.

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Behaviour of trailing wing(s) in echelon formation due to wing twist and aspect ratio

Cited by 12 publications

References 7 publications

Aerodynamic Performance Enhancement of Wing Body Micro UAV Employing Blended Winglet Configuration

Aerodynamic Performance Enhancement of Wing Body Micro UAV Employing Blended Winglet Configuration

Aerodynamic Characteristics of Finite Rectangular Wings in Formation Flight with Ground Effect

Parametric Study on Formation Flying Effectiveness for a Blended-Wing UAV

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