ANALISIS KESTABILAN STATIK PESAWAT UDARA NIR AWAK (PUNA) UNTUK PEMANTAU KEPADATAN LALU LINTAS DENGAN MENGGUNAKAN SOFTWARE XFLR5

Rohmanto, Agus (2022) ANALISIS KESTABILAN STATIK PESAWAT UDARA NIR AWAK (PUNA) UNTUK PEMANTAU KEPADATAN LALU LINTAS DENGAN MENGGUNAKAN SOFTWARE XFLR5. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

One of the uses of unmanned aerial vehicle (UAV) is for traffic monitoring missions. However in designing UAV, it is important to pay attention to the configuration and placement of aircraft components, because they can affect its static stability. Static stability is the tendency or initial response of a system, when disturbed from an equilibrium condition. A statically stable aircraft will be able to generate a moment to return to that state. So that in the design process of UAV, it is necessary to analyze the static stability before entering the manufactur stage. Analysis using XFLR5 software to determine the performance of static stability of UAV on the longitudinal and lateral directional dimensions. UAV modeling using XFLR5 software inputted geometric data from the design in the form of airfoil, wing, vertical tail, horizontal tail, and fuselage. The things that are analyzed are aerodynamic parameters such as CL, Cm, Cl, and Cn which occur with several variations of angle of attack, side slip angle, and horizontal tail incidence angle. Based on the analysis using XFLR5 software, the results are in the form of static stability parameters, such as Cma , CmO , ClB , and CnB . As a result, the aircraft did not meet all the criteria for the longitudinal static stability (Cma < 0 and Cmo > 0) because the value of Cma = -0.0051 while the value of CmO = -0.0162. However, the aircraft has met the criteria for lateral- directional static stability (ClB < 0 and CnB > 0) with a value of ClB = -0.0007 and a value of CnB = 0.0043. Horizontal tail incidence angle (iHT) has an effect on the longitudinal static stability where the more positive the iHT angle given, the more stable on the longitudinal static dimension. The Cl needs of aircraft in cruising flight conditions can be met at a minimum setting of 2° iHT, but further studies are needed by considering other more optimal solutions.

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