ANALISIS KESTABILAN STATIK PESAWAT UDARA
NIR AWAK (PUNA) KARGO DENGAN PAYLOAD 500 KG
MENGGUNAKAN SOFTWARE XFLR5
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
ANTARIKSA, DAVID
Subject
T Technology (General)
Datestamp
2024-05-06 02:39:59
Abstract :
In designing an aircraft, there are many aspects that must be met in order to achieve good flight operational effectiveness, one of which is the static stability aspect of the airplane's flying conditions. The aircraft is declared statically stable if the aircraft can return to its original condition after receiving interference from outside. Static stability analysis must be carried out to determine the static stability characteristics of the Unmanned Aerial Vehicle (UAV) prior to production. The analysis was carried out using XFLR5 software by modeling the Unmanned Aerial Vehicle (UAV), placing the mass value points of each component of the aircraft, as well as analyzing the static stability of the longitudinal, lateral and directional dimensions. The value of the static stability of the longitudinal dimension without a payload is Cma -0,0127/deg and CmO -0,0067 for conditions given a payload of Cma -0,00396/deg and CmO -0,0082. The value of the lateral dimension without payload is ClB - 0,00007/deg and with payload is ClB -0,00009/deg. The value of the directional dimension without payload is CnB 0.0022/deg and the condition with payload is CnB 0.0021/deg. The effect of the incidence angle of the horizontal tail is that the more negative the incidence angle is, the more positive the resulting value will be. Meanwhile, the effect of the incidence angle of the dihedral wing is that the more positive the incidence angle is, the more negative the resulting value will be. Aircraft requirements can be met by applying the incidence angle of the horizontal tail -5° and the incidence angle of the dihedral wing 2°.
In designing an aircraft, there are many aspects that must be met in order to achieve good flight operational effectiveness, one of which is the static stability aspect of the airplane's flying conditions. The aircraft is declared statically stable if the aircraft can return to its original condition after receiving interference from outside. Static stability analysis must be carried out to determine the static stability characteristics of the Unmanned Aerial Vehicle (UAV) prior to production. The analysis was carried out using XFLR5 software by modeling the Unmanned Aerial Vehicle (UAV), placing the mass value points of each component of the aircraft, as well as analyzing the static stability of the longitudinal, lateral and directional dimensions. The value of the static stability of the longitudinal dimension without a payload is Cma -0,0127/deg and CmO -0,0067 for conditions given a payload of Cma -0,00396/deg and CmO -0,0082. The value of the lateral dimension without payload is ClB - 0,00007/deg and with payload is ClB -0,00009/deg. The value of the directional dimension without payload is CnB 0.0022/deg and the condition with payload is CnB 0.0021/deg. The effect of the incidence angle of the horizontal tail is that the more negative the incidence angle is, the more positive the resulting value will be. Meanwhile, the effect of the incidence angle of the dihedral wing is that the more positive the incidence angle is, the more negative the resulting value will be. Aircraft requirements can be met by applying the incidence angle of the horizontal tail -5° and the incidence angle of the dihedral wing 2°.
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