Aerodynamics characteristics of glider GL-1 based on computational fluid dynamics

Amalia, Ema; Moelyadi, Mochammad Agoes; Julistina, R.; Putra, C. A.

doi:10.1088/1742-6596/1130/1/012006

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Cited by 9 publications

(2 citation statements)

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“…The chosen reference vehicle is the GL-01 glider from Amalia et al [21], with three types of control surfaces: ailerons, elevators, and a rudder. The GL-01 original design was scaled down to yield a more realistic wing loading in Uranus' atmosphere of 𝑊/𝑆 = 224.36 N/m 2 .…”

Section: Choice Of Platformmentioning

confidence: 99%

Mission Analysis and Navigation Design for Uranus Atmospheric Flight

Bessette

Mooij

Stam

2022

AIAA SCITECH 2022 Forum

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Section: Choice Of Platformmentioning

confidence: 99%

Mission Analysis and Navigation Design for Uranus Atmospheric Flight

Bessette

Mooij

Stam

2022

AIAA SCITECH 2022 Forum

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“…The availability of several open-source and commercial software makes this plausible. Amalia et al 9 assessed the aerodynamic characteristics of a sailplane using CFD. Angelov and Simeonov 10 reported on the design of a sailplane using modern computational methods.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Analysis and Optimization of Wings for the Jain University Sailplane Using XFLR5

Kakade¹,

Chikkala²,

Reghunath³

et al. 2022

ECS Trans.

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The wing of a sailplane must be designed to conform to specified mission and design requirements. High aerodynamic efficiency and good stall characteristics are some of the design requirements, while achieving level flight at a particular altitude could be a mission requirement. The aerospace engineering students of Jain University set out the task of designing a sailplane capable of flying at an altitude of 7,000 feet. The design task was undertaken using the computational code XFLR5. In the first step, the aerodynamic characteristics of five different airfoils are analyzed considering the effect of altitude. Secondly, the effect of chord length and span on rectangular wing aerodynamics is investigated. The design convergence is obtained for a wing of chord length 1 m and span 20 m. The effect of wing twist on the initially converged design to obtain a more elliptical lift distribution is then performed to obtain optimized designs.

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