Studi Numerik Pemilihan Airfoil Dan Analisa Fenomena Aliran 3D Melewati Sayap Finite Span Untuk Small UAV

Perdana, Fauzi (2019) Studi Numerik Pemilihan Airfoil Dan Analisa Fenomena Aliran 3D Melewati Sayap Finite Span Untuk Small UAV. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Small Unmanned Aerial Vehicle (SUAV) adalah pesawat terbang tanpa awak (PTTA) yang terbang pada ketinggian kurang dari 1100 m dari permukaan tanah, memiliki maximum gross takeoff weight 10 kg, dan kecepatan terbang kurang dari 50 m/s. Salah satu faktor desain penting perancangan Small UAV dengan fixed wing dan pendorong propeller adalah pemilihan airfoil (airfoil selection). Pemilihan profil airfoil menggunakan konsep dasar aerodinamika yang mengarah pada koefisien performa yang menentukan keberlanjutan dan efisiensi dari airfoil yang dipilih. Koefisien yang digunakan yaitu Cl, Cd, dan Cm. Analisa 3D dilakukan setelah analisa 2D pemilihan airfoil untuk mengetahui karakteristik fenomena induced drag pada sayap dengan panjang span tertentu.
Studi numerik yang dilakukan menggunakan Computational Fluid Dynamics dengan menggunakan perangkat lunak XFLR5 untuk mengevaluasi airfoil secara 2D dan Ansys Fluent 17.0 untuk mengevaluasi fenomena trailing vortex dan induced drag pada sayap secara 3D. Pemilihan airfoil dilakukan pada lima jenis airfoil: AH 83-150 Q, E399, E431, E715, dan E662. Koefisien Cl, Cd, dan Cm didapatkan dengan variasi α. Analisa 3D dilakukan pada geometri airfoil yang terpilih dengan finite span. Simulasi kondisi steady menggunakan Reynolds-Averaged-Navier-Stokes (RANS) pada model turbulen Spalart-Allmaras dengan variasi α = 0°, 8°, 12° dan 16°. Post processor visualisasi aliran disekitar sayap dengan kontur tekanan, velocity pathline, tip vortex dan trailing vortex. Analisa juga dilakukan pada koefisien aerodinamik CL, CD, dan CMr dengan variasi α pada sayap finite span.
Berdasarkan penelitian terhadap pemilihan airfoil dan analisa fenomena aliran 3D melewati sayap finite span diperoleh hasil : a) Hasil airfoil selection E431, b) Performa aerodinamik sayap memiliki CL max α=16°, CD max pada α=16°, CL/CD max pada α=8°, CM max dan CMrmax pada α = 16°, c) Penurunan perbedaan tekanan antara sisi upper surface dan lower surface dengan bertambahnya span menunjukkan pengurangan gaya angkat sayap pada daerah disekitar wingtip, d) 3D streamline menunjukkan aliran yang cenderung bergerak dari lower surface ke upper surface body sayap, e) Luasan kontur vorticity magnitude meningkat dengan bertambahnya jarak downstream dibelakang body sayap dan kenaikan α, dan f) Streamline pada wingtip sisi upper surface dan lower surface body sayap mengalami perbedaan orientasi dengan aliran kecepatan freestream dan cenderung berbentuk curl.
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Small Unmanned Aerial Vehicle (SUAV) is an unmanned
aircraft which flies at an altitude of less than 1100 m above ground
level, has a maximum gross takeoff weight of 10 kg, and a flying
speed of less than 50 m / s. One important design factor for the
design of Small UAVs with fixed wing and propeller propulsion is
airfoil selection. The selection of airfoil profiles uses the basic
aerodynamic concepts that lead to performance coefficients that
determine the sustainability and efficiency of the selected airfoil.
The coefficients used are Cl, Cd, and Cm. 3D analysis is carried out
after 2D analysis of airfoil selection to determine the
characteristics of induced drag phenomena on wings with a certain
span length.
Numerical studies were carried out using Computational
Fluid Dynamics using XFLR5 software to evaluate 2D airfoils and
Ansys Fluent 17.0 to evaluate the phenomenon of trailing vortex
and induced drag on the wing in 3D. The choice of airfoil was
carried out on five airfoil types: AH 83-150 Q, E399, E431, E715,
and E662, respectively. The coefficients of Cl, Cd, and Cm are
obtained by variations of α. 3D analysis is performed on selected
airfoil geometry with finite span. Steady condition simulations use
Reynolds-Averaged-Navier-Stokes (RANS) on the Spalart-
Allmaras turbulent model with variations of α 0 °, 8 °, 12 ° and
16 °, respectively. Post processor visualizes the flow around the
wing with the pressure contour, velocity pathline, vortex tip and
trailing vortex. Analysis was also carried out on the CL, CD, and CMr aerodynamic coefficients with variations of α on the finite span
wing.
Based on research on the selection of airfoils and analysis
of the phenomenon of 3D flow through the finite span wing, the
results are obtained: a) The airfoil selection result is E431, b) The
wing aerodynamic performance has a maximum CL at α = 16 °, the
maximum CD at α = 16 °, CL / CD which is high at α = 8 °, CM and
CMr which is high at α = 16 °, c) Decreasing the difference in
pressure between the upper surface and lower surface with
increasing span shows a reduction in wing lift in the area around
the wingtip, d) Streamlined 3D shows flow that tends moving from
lower surface to upper surface body wing, e) Extent of vorticity
magnitude increases with increasing X / c values behind wing body
and α, and f) Streamline on wingtip upper surface and lower
surface body wing experiencing different orientation with
freestream velocity and tends to be curl.

Item Type:	Thesis (Undergraduate)
Additional Information:	RSM 620.106 4 Per s-1 2019
Uncontrolled Keywords:	Airfoil, Computational Fluid Dynamics, Induced drag, UAV, Trailing vortex
Subjects:	Q Science > QC Physics > QC151 Fluid dynamics T Technology > TJ Mechanical engineering and machinery T Technology > TJ Mechanical engineering and machinery > TJ820 Wind power
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Fauzi Perdana
Date Deposited:	05 Jan 2022 04:11
Last Modified:	05 Jan 2022 04:11
URI:	http://repository.its.ac.id/id/eprint/61963

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