Simulasi Numerik Pengaruh Angle Of Attack Pada Perancangan Front Wing Mobil Formula Student Sapuangin ITS Pada Kondisi Berbelok

Suteja, I Gede Rudy Artha (2021) Simulasi Numerik Pengaruh Angle Of Attack Pada Perancangan Front Wing Mobil Formula Student Sapuangin ITS Pada Kondisi Berbelok. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

	Text 10211710010039-Undergraduate_Thesis.pdf - Accepted Version Restricted to Repository staff only until 1 October 2023. Download (4MB) | Request a copy
	Text 10211710010039-Undergraduate_Thesis.pdf - Accepted Version Restricted to Repository staff only Download (4MB) | Request a copy
	Text 10211710010039-Undergraduate_Thesis.pdf Restricted to Repository staff only Download (4MB) | Request a copy
	Text 10211710010039-Undergraduate_Thesis.pdf Restricted to Repository staff only Download (4MB) | Request a copy

Abstract

Saat kendaraan melewati tikungan, medan aliran udara yang diamati dari frame of reference kendaraan menjadi melengkung. Kondisi ini mengakibatkan sudut aliran relatif dan kecepatan freestream udara berubah baik selebar maupun sepanjang bodi. Metode Large Eddy Simulation digunakan untuk mensimulasikan bentuk multi element airfoil (Front Winglet) dengan variasi Angle of Attack (AoA) pada bagian 1st dan 2nd flap dengan membuat domain yang pola alirannya mendekati kondisi aktual ketika bodi sedang berbelok. Kecepatan pada inlet diatur pada nilai 11.11 m/s dimana merupakan rata-rata kecepatan mobil formula Sapuangin Speed 6 pada event skidpad. Pada radius lintasan selebar 15.25m dan Reynolds number sebesar 9.8 × 105 akan dianalisa performa front wing dengan variasi Angle of Attack terhadap perubahan drag force, down force, nilai koefisien lift (CL) dan koefisien drag (CD) serta pengaruhnya terhadap perubahan drag force dan koefisien drag (CD) pada roda depan mobil. Setelah mendapatkan konfigurasi AoA front wing dengan CL/CD tertinggi front wing akan dipasang pada mobil formula Sapuangin Speed 6 untuk dianalisa performanya.
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As a vehicle through a corner, the flowfield observed from the vehicle’s frame of reference becomes curved. This condition results in the relative flow angle and freestream velocity changing both across the width and along the length of the body. Wall-resolved Large Eddy Simulations were used to simulate multi element airfoil (Front Winglet) shape with Angle of Attack (AoA) variation on 1st and 2nd flap by making a domain whose flow stream close to actual condition of a cornering object. Inlet Velocity was set at 11.11 m/s where this is a mean velocity of formula Sapuangin Speed 6 car at skidpad event. On a track with 15.25m width of diameter and with Reynolds number 9.8 × 105 the front wing performance will be analyzed with Angle of Attack variation toward drag force change, down force, coefficient lift (CL) value and coeficcient drag (CD) value and its effect towards drag force change and drag coefficient (CD) value at car’s front wheels. After getting the highest front wing’s AoA CL/CD ratio, the front wing will be installed to formula Sapuangin Speed 6 car to analyze the performance.

Item Type:	Thesis (Undergraduate)
Uncontrolled Keywords:	Angle of Attack, Front Wing, Koefisien lift, koefisien drag, down force, drag force, Ban, Sapuangin Speed 6, Kecepatan Freestream, Tekanan statis.============================================================================================================= Angle of Attack, Front Wing, lift coefficient, drag coefficient, down force, drag force, wheels, Sapuangin Speed 6, Freestream velocity, Static pressure.
Subjects:	T Technology > TA Engineering (General). Civil engineering (General) > TA357 Computational fluid dynamics. Fluid Mechanics T Technology > TL Motor vehicles. Aeronautics. Astronautics T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic.
Divisions:	Faculty of Vocational > Mechanical Industrial Engineering (D4)
Depositing User:	I gede rudy artha suteja
Date Deposited:	05 Aug 2021 21:15
Last Modified:	05 Aug 2021 21:15
URI:	http://repository.its.ac.id/id/eprint/84914

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