Aircraft performance of Kenyalang fuel cell UAV

Noor Idayu Mohd Tahir; Wahyu Kuntjoro; Thomas Arthur Ward

doi:10.4028/www.scientific.net/AMM.393.338

Aircraft performance of Kenyalang fuel cell UAV

Noor Idayu Mohd Tahir, Wahyu Kuntjoro, Thomas Arthur Ward

School of Engineering & Physical Sciences

University of Malaya

Research output: Contribution to journal › Article › peer-review

1 Citation (Scopus)

Abstract

Kenyalang is a fuel cell powered Unmanned Aerial Vehicle (UAV) developed by Universiti Teknologi MARA (UiTM). This paper discusses the aircraft performances analysis of Kenyalang. Computational Fluid Dynamic (CFD) using Numeca software had been performed to obtain the aerodynamics characteristic of the Kenyalang UAV in the form of lift (CL) and drag (CD) coefficients. Unstructured mesh and standard one - equation turbulence model, and Spalart- Allmaras selected in the simulation. Lift coefficients (CL) and drag coefficients (CD) were studied at flight condition of Mach 0.08 (~26 m/s) at different angles of attack, α. The CFD data results were used to obtain Stall Speed, Take off Distance and Rate of Climb, and the results are shown in this paper.

Original language	English
Pages (from-to)	338-343
Number of pages	6
Journal	Applied Mechanics and Materials
Volume	393
DOIs	https://doi.org/10.4028/www.scientific.net/AMM.393.338
Publication status	Published - 2013
Event	International Conference on Advances in Mechanical Engineering 2013 - Malacca, Malaysia Duration: 28 Aug 2013 → 29 Aug 2013

Keywords

Aerodynamic
Aircraft performance
CFD (Computational Fluid Dynamic)
Lift coefficient and drag coefficient
Unmanned Aerial Vehicles(UAV)-kenyalang I

ASJC Scopus subject areas

Engineering(all)

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Cite this

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title = "Aircraft performance of Kenyalang fuel cell UAV",

abstract = "Kenyalang is a fuel cell powered Unmanned Aerial Vehicle (UAV) developed by Universiti Teknologi MARA (UiTM). This paper discusses the aircraft performances analysis of Kenyalang. Computational Fluid Dynamic (CFD) using Numeca software had been performed to obtain the aerodynamics characteristic of the Kenyalang UAV in the form of lift (CL) and drag (CD) coefficients. Unstructured mesh and standard one - equation turbulence model, and Spalart- Allmaras selected in the simulation. Lift coefficients (CL) and drag coefficients (CD) were studied at flight condition of Mach 0.08 (~26 m/s) at different angles of attack, α. The CFD data results were used to obtain Stall Speed, Take off Distance and Rate of Climb, and the results are shown in this paper.",

keywords = "Aerodynamic, Aircraft performance, CFD (Computational Fluid Dynamic), Lift coefficient and drag coefficient, Unmanned Aerial Vehicles(UAV)-kenyalang I",

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AU - Mohd Tahir, Noor Idayu

AU - Kuntjoro, Wahyu

AU - Ward, Thomas Arthur

PY - 2013

Y1 - 2013

N2 - Kenyalang is a fuel cell powered Unmanned Aerial Vehicle (UAV) developed by Universiti Teknologi MARA (UiTM). This paper discusses the aircraft performances analysis of Kenyalang. Computational Fluid Dynamic (CFD) using Numeca software had been performed to obtain the aerodynamics characteristic of the Kenyalang UAV in the form of lift (CL) and drag (CD) coefficients. Unstructured mesh and standard one - equation turbulence model, and Spalart- Allmaras selected in the simulation. Lift coefficients (CL) and drag coefficients (CD) were studied at flight condition of Mach 0.08 (~26 m/s) at different angles of attack, α. The CFD data results were used to obtain Stall Speed, Take off Distance and Rate of Climb, and the results are shown in this paper.

AB - Kenyalang is a fuel cell powered Unmanned Aerial Vehicle (UAV) developed by Universiti Teknologi MARA (UiTM). This paper discusses the aircraft performances analysis of Kenyalang. Computational Fluid Dynamic (CFD) using Numeca software had been performed to obtain the aerodynamics characteristic of the Kenyalang UAV in the form of lift (CL) and drag (CD) coefficients. Unstructured mesh and standard one - equation turbulence model, and Spalart- Allmaras selected in the simulation. Lift coefficients (CL) and drag coefficients (CD) were studied at flight condition of Mach 0.08 (~26 m/s) at different angles of attack, α. The CFD data results were used to obtain Stall Speed, Take off Distance and Rate of Climb, and the results are shown in this paper.

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KW - Aircraft performance

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KW - Lift coefficient and drag coefficient

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T2 - International Conference on Advances in Mechanical Engineering 2013

Y2 - 28 August 2013 through 29 August 2013

ER -

Aircraft performance of Kenyalang fuel cell UAV

Abstract

Keywords

ASJC Scopus subject areas

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