Simulasi Numerik Batas Kecepatan Flutter Dan Divergence Pada Wingbox Kanan Cruciform tail Pesawat N219

Setyabudi, Fadhil Ramadhan (2026) Simulasi Numerik Batas Kecepatan Flutter Dan Divergence Pada Wingbox Kanan Cruciform tail Pesawat N219. Diploma thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Flutter merupakan fenomena ketidakstabilan aeroelastik yang terjadi akibat interaksi antara gaya aerodinamika, elastisitas struktur, dan inersia, yang dapat menyebabkan osilasi struktur meningkat secara signifikan dan berpotensi menimbulkan kegagalan struktur. Fenomena ini menjadi salah satu pertimbangan penting dalam perancangan dan evaluasi struktur pesawat untuk memastikan batas operasi penerbangan tetap berada dalam kondisi aman. Penelitian ini bertujuan untuk menganalisis kecepatan terjadinya flutter dan divergence serta memetakan batas kestabilan aeroelastik pada struktur wingbox kanan cruciform tail pesawat N219 melalui pendekatan simulasi numerik. Analisis dilakukan dengan menggunakan pendekatan aeroelastik linier pada rezim aliran subsonik dengan variasi Mach number sebesar 0,3 hingga 0,7. Tahapan penelitian meliputi analisis frekuensi alami dan mode shape struktur, kemudian dilanjutkan dengan pembuatan kurva V–g dan V–f untuk mengidentifikasi kondisi ketidakstabilan aeroelastik. Hasil penelitian menunjukkan bahwa fenomena flutter terjadi pada mode ketiga dengan kecepatan flutter sebesar 700,694 m/s pada Mach number 0,3 dan menurun menjadi 627,123 m/s pada Mach number 0,7, menunjukkan tren penurunan seiring meningkatnya Mach number. Sementara itu, fenomena divergence terjadi pada mode pertama yang didominasi oleh deformasi lentur, dengan kecepatan divergence sebesar 1691,388 m/s pada Mach 0,3 dan menurun menjadi 1240,632 m/s pada Mach 0,7, yang juga menunjukkan tren penurunan terhadap peningkatan Mach number.
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Flutter is an aeroelastic instability phenomenon that occurs due to the interaction between aerodynamic forces, structural elasticity, and inertia, which can lead to significantly increasing structural oscillations and potentially result in structural failure. This phenomenon is one of the key considerations in aircraft structural design and evaluation to ensure that flight operating limits remain within safe conditions. This study aims to analyze the flutter and divergence speeds and to map the aeroelastic stability boundaries of the right wingbox structure of the cruciform tail of the N219 aircraft through a numerical simulation approach. The analysis is carried out using a linear aeroelastic approach in the subsonic flow regime with Mach number variations ranging from 0.3 to 0.7. The research stages include the analysis of natural frequencies and structural mode shapes, followed by the construction of V–g and V–f curves to identify aeroelastic instability conditions. The results show that flutter occurs in the third mode with a flutter speed of 700.694 m/s at Mach number 0.3, decreasing to 627.123 m/s at Mach number 0.7, indicating a downward trend as the Mach number increases. Meanwhile, divergence occurs in the first mode, which is dominated by bending deformation, with a divergence speed of 1691.388 m/s at Mach number 0.3, decreasing to 1240.632 m/s at Mach number 0.7, also showing a decreasing trend with increasing Mach number.

Item Type:	Thesis (Diploma)
Uncontrolled Keywords:	Aeroelastik, Divergence, Flutter, Pesawat N219, Wingbox, Aeroelasticity, Divergence, Flutter, N219 Aircraft, Wingbox.
Subjects:	T Technology > TA Engineering (General). Civil engineering (General) > TA645 Structural analysis (Engineering)
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Fadhil Ramadhan Setyabudi
Date Deposited:	31 Jul 2026 06:48
Last Modified:	31 Jul 2026 06:48
URI:	http://repository.its.ac.id/id/eprint/140525

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