COMPUTATIONAL FLUID DYNAMICS BASED WINGLET DESIGN AND ANALYSIS OF GL-1 GLIDER
Winglet is the most effective device installed in wing tip to reduce induced drag which is the second largest contribution of drag especially in a low-speed aircraft. The drag is from wingtip vortex. In the previous study, GL-1 have not added yet by winglet and the aerodynamic efficiency was 27 o...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/41567 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | Winglet is the most effective device installed in wing tip to reduce induced
drag which is the second largest contribution of drag especially in a low-speed
aircraft. The drag is from wingtip vortex. In the previous study, GL-1 have not
added yet by winglet and the aerodynamic efficiency was 27 or equal to 11.7 km
maximum range. However, that value was below the conceptual design value which
is 30 or equal to 13.7 km maximum range. The objective of the study is to increase
aerodynamic efficiency of GL-1 to 30 by introducing the winglet. The problem a is
determining winglet geometry that fulfill design target. So, the study of parametric
method is carried out including winglet height, sweep angle, and taper ratio. To
produce desired aerodynamic characteristics from the winglet, computational fluid
dynamics method solving Reynold Averaged Shear Stress coupled with Shear
Stress Transport and Gamma-Theta transition model is used. After winglet is
installed to GL-1, the lift coefficient, CL, increases by 3.4106 percent, the drag
coefficient, CD, decreases by 3.2086 percent, and aerodynamic efficiency
(CL/CD).is increased by 6.8366 percent as well as the maximum range increases
from 11.7 to 12.5 km. |
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