Airflow Numerical Analysis on Low Speed Unmanned Aerial Vehicle Winglet
Reliability and stability of unmanned aircraft or Unmanned Aerial Vehicle (UAV) is strongly influenced by the design of aircraft, especially in the shape of the wings toward the flying characteristics. The effect of the superior aerodynamic character can improve the aircraft performance,...
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id-ugm-repo.1378592016-11-15T02:03:39Z https://repository.ugm.ac.id/137859/ Airflow Numerical Analysis on Low Speed Unmanned Aerial Vehicle Winglet Winarto, E.W. Sakarinto, W. Wibowo, S.B. Elycia, L. Aerospace Engineering Aircraft Performance and Flight Control Systems Reliability and stability of unmanned aircraft or Unmanned Aerial Vehicle (UAV) is strongly influenced by the design of aircraft, especially in the shape of the wings toward the flying characteristics. The effect of the superior aerodynamic character can improve the aircraft performance, save the fuel and maintain flying stability of the aircraf t. One improvement on aerodynamic character is the addition of winglets. The winglet will increase lift and reduce drag with a more compact wingspan dimension due to the reduction of wing tip vortex effect. Nevertheless, winglets are widely used on passenger aircraf t. Meanwhile, it is rarely used on unmanned aerial vehicle. . Research on the character of winglets for improving UAV’s performance becomes particularly important given the limited time of UAV which has become a major obstacle. With increased flight efficiency obtained from winglet configuration, it is expected that UAV will be able to fly longer. This study will test characteristic of winglets shape on the wings of an aircraft through numerical modeling to gain aerodynamic flow visualization. From the modeling, it is shown that the use of winglet is able to reduce the effects of with tip vortex. The use of sloping outwards rounded winglet will give a significant increase in the lift force. Winglet slope projections towards the horizontal line will increase the lift force. For flying conditions, the highest efficiency value is in the Angle of Attack 7.50. Keywords : UAV, wing tip vortex, winglet, numeric method, CFD 2016-10-04 Conference or Workshop Item PeerReviewed application/pdf en https://repository.ugm.ac.id/137859/1/Airflow%20Numerical%20Analysis%20on%20Low%20Speed.pdf Winarto, E.W. and Sakarinto, W. and Wibowo, S.B. and Elycia, L. (2016) Airflow Numerical Analysis on Low Speed Unmanned Aerial Vehicle Winglet. In: 6th International Symposium On Technology For Sustainability (ISTS 2016), Yogyakarta. http://www.ists.sv.ugm.ac.id |
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Aerospace Engineering Aircraft Performance and Flight Control Systems Winarto, E.W. Sakarinto, W. Wibowo, S.B. Elycia, L. Airflow Numerical Analysis on Low Speed Unmanned Aerial Vehicle Winglet |
description |
Reliability and stability of unmanned aircraft
or Unmanned Aerial Vehicle (UAV) is strongly
influenced by the design of aircraft, especially in the
shape of the wings toward the flying characteristics. The
effect of the superior aerodynamic character can
improve the aircraft performance, save the fuel and
maintain flying stability of the aircraf t. One
improvement on aerodynamic character is the addition
of winglets. The winglet will increase lift and reduce
drag with a more compact wingspan dimension due to
the reduction of wing tip vortex effect. Nevertheless,
winglets are widely used on passenger aircraf t.
Meanwhile, it is rarely used on unmanned aerial
vehicle. . Research on the character of winglets for
improving UAV’s performance becomes particularly
important given the limited time of UAV which has
become a major obstacle. With increased flight efficiency
obtained from winglet configuration, it is expected that
UAV will be able to fly longer. This study will test
characteristic of winglets shape on the wings of an
aircraft through numerical modeling to gain
aerodynamic flow visualization. From the modeling, it is
shown that the use of winglet is able to reduce the
effects of with tip vortex. The use of sloping outwards
rounded winglet will give a significant increase in the lift
force. Winglet slope projections towards the horizontal
line will increase the lift force. For flying conditions,
the highest efficiency value is in the Angle of Attack 7.50.
Keywords : UAV, wing tip vortex, winglet, numeric
method, CFD |
format |
Conference or Workshop Item PeerReviewed |
author |
Winarto, E.W. Sakarinto, W. Wibowo, S.B. Elycia, L. |
author_facet |
Winarto, E.W. Sakarinto, W. Wibowo, S.B. Elycia, L. |
author_sort |
Winarto, E.W. |
title |
Airflow Numerical Analysis on Low Speed
Unmanned Aerial Vehicle Winglet |
title_short |
Airflow Numerical Analysis on Low Speed
Unmanned Aerial Vehicle Winglet |
title_full |
Airflow Numerical Analysis on Low Speed
Unmanned Aerial Vehicle Winglet |
title_fullStr |
Airflow Numerical Analysis on Low Speed
Unmanned Aerial Vehicle Winglet |
title_full_unstemmed |
Airflow Numerical Analysis on Low Speed
Unmanned Aerial Vehicle Winglet |
title_sort |
airflow numerical analysis on low speed
unmanned aerial vehicle winglet |
publishDate |
2016 |
url |
https://repository.ugm.ac.id/137859/1/Airflow%20Numerical%20Analysis%20on%20Low%20Speed.pdf https://repository.ugm.ac.id/137859/ http://www.ists.sv.ugm.ac.id |
_version_ |
1681234181705695232 |