Experimental study of UTM-LST generic half model transport aircraft

Ujang, M I; Mat, Shabudin; Perumal, Kannan; Nasir, Mohd Nazri Mohd

doi:10.1088/1757-899x/152/1/012007

IOP Conf. Ser.: Mater. Sci. Eng.

2016

DOI: 10.1088/1757-899x/152/1/012007

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Experimental study of UTM-LST generic half model transport aircraft

M I Ujang

Shabudin Mat

Kannan Perumal

et al.

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“…Initially A grid Independence Test was performed for the given simulation setup, and the changing parameter was the fineness of the Mesh Cell (Starting from 1 -9) where 1 is coarse and 9 is the most finest, then following values of Number of Cells were obtained, as in table4, where the number of Cells are in Millions and the Drag Coefficient values were observed, and thus looking at figure 8 it was observed that the mesh starts to converge fromS E3S Web of Conferences 477, 00029 (2024) https://doi.org/10.1051/e3sconf/202447700029…”

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Aerodynamics of a wing body with different Winglet Cant Angle

Bakhai,

Mat,

Musa

2024

E3S Web Conf.

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Current aircraft was designed with winglet at the tip. Winglets reduce the drag and improve fuel efficiency and range. The winglets have been in use for nearly 90 years, but it have been remained fixed. This paper presents the effects of winglet Cant angle on the aerodynamic characteristics of the wing. Winglet Cant Angle (WCA) is the angle between the vertical exis and the winglet. Computational Fluid Dynamics (CFD) has been used to simulate the Cant angles at constant angle of attack of 0⁰. In this paper the Cant angle was varied from 105⁰, 88⁰, 75⁰, 60⁰, 50⁰, 45⁰, 35⁰ and the simulation works were performed at three different Flight levels of Sea level, 10000 and 15000 meters. The analysis analysis at 100 m/s velocity shows that Cant angle of 45⁰ is the best performing Winglet while Cant 60⁰ is the lowest performance in overall lift to drag Ratio. Similar results were obtained when Turbulent Kinematic Viscosity were measured at 20 m behind the wing. Flow visualization also showed the similar results Cant angle 450 is the best performance compared to other angles. For the best performing winglet, the lift to drag Ratio was lowest for perpendicular crosswinds. This study shows the effect of only winglet cant angle, however other factors involved to impact the performance of winglet are, Winglet height, winglet sweep angle, Winglet Cant angle, Winglet Toe angle, and crosswinds. To implement the best overall drag coefficient winglet, the optimization must be done mid-air. While calculating the parameters, the best most optimized winglet can be chosen for cruising flight level.

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confidence: 99%

Aerodynamics of a wing body with different Winglet Cant Angle

Bakhai,

Mat,

Musa

2024

E3S Web Conf.

View full text Add to dashboard Cite

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Semi-span wind tunnel testing without conventional peniche

Skinner

Zare‐Behtash

2017

Exp Fluids

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Experimental study of UTM-LST generic half model transport aircraft

Cited by 2 publications

References 2 publications

Aerodynamics of a wing body with different Winglet Cant Angle

Aerodynamics of a wing body with different Winglet Cant Angle

Semi-span wind tunnel testing without conventional peniche

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