Analysis of aerodynamic characteristics using the vortex lattice method on twin tail boom unmanned aircraft

Septiyana, Angga; Hidayat, Kurnia; Rizaldi, Ardian; Ramadiansyah, M. L.; Ramadhan, Redha Akbar; Suseno, Prasetyo Ardi Probo; Jayanti, Eries Bagita; Atmasari, Novita; Rasyadi, A.

doi:10.1063/5.0002337

Cited by 10 publications

(5 citation statements)

References 6 publications

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“…Peneltian yang berkaitan dengan analisis aerodinamika dengan menggunakan perangkat lunak XFLR5 telah dilakukan oleh [1], [2] dan [3]. Pada penelitian yang dilakukan menunjukkan hasil simulasi XFLR5 dapat dijadikan untuk menganalisis karakteristik aerodinamika.…”

Section: Pendahuluanunclassified

“…Penelitian yang dilakukan oleh Dantsker dan Vahora [1] membandingkan methode numerik untuk mengetahui karakteristik aerodinamika pada pesawat yang dibuat. Sedangkan penelitian yang dilakukan oleh [3] menggunakan metode Vortex Lattice Method untuk mengetahui karakteristik aerodinamika pesawat dengan tipe twin tail boom. Akan tetapi pada hasil simulasi numerik karakteristik aerodinamika menunjukkan bahwa data luaran yang dihasilkan merupakan kurva linear.…”

Section: Pendahuluanunclassified

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Terapan Fungsi Sigmoid Untuk Menentukan Nilai Maksimal Koefisien Gaya Angkat Dan Sudut Stall Pada Kurva Linear Cl Terhadap Α

Septiyana

et al. 2022

puc

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Karya tulis ilmiah ini membahas tentang terapan fungsi sigmoid untuk menentukan nilai maksimal gaya angkat dan sudut stall pada pesawat berdasarkan hasil simulasi dengan menggunakan perangkat lunak XFLR5.Nilai maksimal gaya angkat dan sudut stall pada sebuahpesawatmerupakankomponenyangharusdiketahuiagarpesawattidakmengalamistall. Dimana pada saat pesawat sudah mencapai sudut stall pesawat akan kehilangan gaya angkat dan menyebabkan pesawat jatuh. Perangkat lunak XFLR5 digunakan untuk mensimulasikan sertauntukmendapatkankurvakoefisiengayaangkat CLterhadapsudutserang α. Hasilsimulasi dengan menggunakan perangkat lunak XFLR5 menunjukkan grafik CL terhadap α bersifat linear yang artinya tidak dapat diketahui dimana koefisien gaya angkat maksimal dan sudut serang dimana pesawat mengalami stall. Hasil penelitian ini fungsi sigmoid ini dapat diterapkan untuk menentukan nilai maksimal koefisien gaya angkat dan sudut stall dari pesawat. Penelitian yang dilakukan dengan memilih nilai transition rate M sebesar 0.8 diperoleh hasilnilai koefisien gaya angkat maksimal 1.2648 dan sudut stall sebesar 13◦

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Section: Pendahuluanunclassified

Terapan Fungsi Sigmoid Untuk Menentukan Nilai Maksimal Koefisien Gaya Angkat Dan Sudut Stall Pada Kurva Linear Cl Terhadap Α

Septiyana

et al. 2022

puc

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“…VLM models the disturbance formed on a wing, by summation of vortices, and the strength of a single vortex is examined by an imposed boundary condition. VLM is selected for current analysis because the flow is considered inviscid and potential, Chethan R. Patil et al [16], and additionally only induced drag can be measured, A. Septiyana et al [17]. Oliviu Sugar Gabor et al [18] preferred XFLR5 to compare the aerodynamic characteristics of a wing with the non-linear VLM method and experimental's.…”

Section: Wing Design and Analysismentioning

confidence: 99%

Airfoil Analysis and Effect of Wing Shape Optimization on Aerodynamic Parameters in a Steady Flight

Oza¹,

Vala²

2021

GJRE

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The work in this paper deals with reconstructing and optimizing the wing geometry of an Unmanned Combat Aerial Vehicle for improved performance and reviewing the impact of the modification on flight parameters in a steady flight. The behavior of airfoils at planned flight conditions under I.S.A. is checked in XFLR5 software. Following up by 2-D CFD and boundary layer analysis of former and new airfoil, dimensions of the wing are re-developed, keeping the fuselage and tail structure same. The existing wing and the optimized wing design is analyzed by Vortex Lattice Method and Triangular Panel Method, with an objective to make the shape of the wing aerodynamically suitable for an increased Lift to Drag ratio and thereby minimizing drag coefficients.

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“…XFLR5 software can estimate the aerodynamic coefficients with appropriate accuracy by VLM. Several research projects have been performed to calculate aerodynamic coefficients, including lift and drag [21,22]. Agten from Delft university of technology, in the master's thesis, used VLM and XFLR5 software to calculate an aerodynamic coefficient of airborne system for Airborne Wind Energy Applications [23].…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of a tethered-glider for generating electrical-renewable energy using the pumping cycle method

2022

IJM

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The issue of energy generation from wind is considered one of the main ways to develop renewed energy in some areas worldwide. The important point in generating energy from wind is the permanent wind availability, which is called the existence of effective wind. According to studies, there is no effective wind at ground level in many areas of the world, while this wind is available at altitude. The Accessibility of wind in altitude has led to the development of various technologies in energy production from airborne systems. In this research, airborne wind energy systems technologies have been investigated, and a tethered-glider was designed and analyzed using analytical methods for energy generation at a 200-meter altitude. The main factor in designing a glider is the optimal ratio of lift to drag coefficient; For calculating lift to drag coefficient, the vortex lattice method (VLC) is used in this paper. The results illustrate that a glider with a wingspan of 5.2 meters can produce a maximum of 10 kilowatts of energy over one cycle. Increasing this ratio can increase energy production efficiency.

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Analysis of aerodynamic characteristics using the vortex lattice method on twin tail boom unmanned aircraft

Cited by 10 publications

References 6 publications

Terapan Fungsi Sigmoid Untuk Menentukan Nilai Maksimal Koefisien Gaya Angkat Dan Sudut Stall Pada Kurva Linear Cl Terhadap Α

Terapan Fungsi Sigmoid Untuk Menentukan Nilai Maksimal Koefisien Gaya Angkat Dan Sudut Stall Pada Kurva Linear Cl Terhadap Α

Airfoil Analysis and Effect of Wing Shape Optimization on Aerodynamic Parameters in a Steady Flight

Design and analysis of a tethered-glider for generating electrical-renewable energy using the pumping cycle method

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