Fabrication of UiTM’s Energy Glider

Zurriati Mohd Ali; Jasmine Demi Danny Jabing; Zulhilmy Sahwee

doi:10.24191/jaeds.v3i1.56

Authors

Zurriati Mohd Ali School of Mechanical Engineering, Universiti Teknologi MARA, Shah Alam Selangor, Malaysia.
Jasmine Demi Danny Jabing School of Mechanical Engineering, College of Engineering, Universiti Teknologi MARA, Shah Alam, Malaysia
Zulhilmy Sahwee Universiti Kuala Lumpur, Malaysian Institute of Aviation Technology (UniKL MIAT), Dengkil, Selangor, Malaysia

DOI:

https://doi.org/10.24191/jaeds.v3i1.56

Keywords:

Glider, lifting surface; kfm-5A, fabrication, CFD

Abstract

Glider is a fixed-wing aircraft which does not depend on the engine. A glider can fly for an extended period depending on the design and area of the lifting surface. Just like any other aircrafts, the design of wings is crucial to produce lift force to keep aircraft in the air. Gliders have long wings and is designed to be lightweight which allows it to have a high lift-to-drag ratio (L/D) to glide at a long distance. The maximum lift-to-drag ratio, 〖(L/D〗_max) can indicate how far the glider will glide as it is one of the most important performance parameters. This project aims to design, build, and fly an energy glider. Prior on the design of the energy glider, statistical analysis has been done by comparing data from many studies to aid in determining the initial values of the glider. Then, the general design of the energy glider has been decided during the preliminary design. To support the design decision made, ANSYS Fluent software has been used to study flow of air over KFm-5A aerofoil profile which has been chosen during the early stages of design. The model of the energy glider was then designed in CATIA V5 software with a wingspan of 1.52 m and fuselage length of 0.69 m. Lastly, flight test was conducted to achieve the project’s objective. During the flight test, the glider reached a ceiling height of approximately 300 m and obtained a velocity of 144 km/h. The analysis of the glider performance will be used as an aircraft data for future research.

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