TY  - CONF
SN  - 0094243X
PB  - American Institute of Physics Inc.
Y1  - 2020///
VL  - 2228
UR  - https://www.scopus.com/inward/record.uri?eid=2-s2.0-85096441483&doi=10.1063%2f5.0000899&partnerID=40&md5=c42503074331fe43b8d6f5740b002176
A1  - Bintara, R.D.
A1  - Sarmaman, T.
A1  - Andoko
A1  - Mardji
A1  - Wulandari, R.
A1  - Shaharun, M.S.
A1  - Pradica, D.R.
AV  - none
TI  - The winglet design for blended wing body (BWB-UAV) using computational fluid dynamic (CFD) approach
ID  - scholars13236
N1  - cited By 1; Conference of 2019 Annual International Conference on Renewable Energy, ICORE 2019 ; Conference Date: 9 August 2019 Through 10 August 2019; Conference Code:164592
N2  - Unmanned Aerial Vehicles (UAVs) are unmanned aircraft that can fly from long distances using remote control or flying with an autonomous system. Blended Wing Body (BWB) is one of the UAVs being developed. In this research, the angle of the winglet and air velocity is varied to performance of the BWB-UAV lift force (Lift), drag force (drag) and moment. The Computational Fluid Dynamic (ANSYS 17.0 Fluent) approach is used to simulate the BWB-UAV model that was made. Furthermore, the results of the lift, drag and moment are recorded and analyzed. According to the results, it show that the bend angle of 0° (without wings) gives a fairly large amount of turbulent air to the wing tips, while at an angle of 45° the air flow on the wings of the aircraft is lean distributed. In addition, the pressure on the BWB-UAV increases proportionally in speeds of air and bend angle of winglet. In this study, it is distinct that the lift is inversely proportional to the drag value where the increasing lift can also increasing the drag value. © 2020 American Institute of Physics Inc.. All rights reserved.
ER  -