Studi Ekperimental Karakteristik Aerodinamik Aliran Melintasi Silinder Sirkular Dengan Bodi Pengganggu Airfoil Simestris NACA 0012, NACA 0018, Dan NACA 0024

Reiza, Muhammad Naufal (2023) Studi Ekperimental Karakteristik Aerodinamik Aliran Melintasi Silinder Sirkular Dengan Bodi Pengganggu Airfoil Simestris NACA 0012, NACA 0018, Dan NACA 0024. Other thesis, Institut Teknologi Sepuluh Nopember.

Text 02111940000020-Undergraduate_Thesis.pdf - Accepted Version Restricted to Repository staff only until 1 October 2025. Download (3MB) | Request a copy

Abstract

Dalam dunia teknik khususnya bidang mekanika fluida, perhitungan mengenai suatu aliran yang melalui sebuah saluran sering dilakukan, misalkan saja memprediksi karakteristik aliran yang terjadi pada aliran yang melintasi suatu saluran. Silinder sirkular merupakan salah satu bentuk geometri dari bluff body yang paling sering digunakan dan memiliki drag force yang besar dikarenakan separasi yang terbentuk lebih awal sehingga menghasilkan wake yang lebih besar. Semakin cepat separasi aliran terbentuk, maka luas daerah wake semakin besar. Besarnya drag force sangat mempengaruhi efisiensi kerja. Oleh karena itu cara untuk mereduksi drag force yaitu dengan cara melakukan manipulasi medan aliran. Salah satu cara memanipulasi medan aliran yaitu dengan menggunakan metode passive flow control. Penelitian ini membahas tentang pengaruh penambahan bodi pengganggu airfoil di diepan silinder sirkular. Penelitian ini dilakukan secara eksperimental pada silinder sirkular (D = 36 mm) dengan disturbance body berupa airfoil (NACA 0012, NACA 0018, NACA 0024) dengan angle of attack sebesar 5° diletakkan didepan silinder sirkular dalam sub-sonic wind tunnel berukuran (h = 200 mm, z = 200 mm, x = 2000 mm), yang diuji dengan variasi jarak S/D = 1,6 ; 2,0 ; 2,4 ; 2,8. Dalam penelitian ini, tekanan diukur menggunakan pressure taps yang dipasang pada permukaan silinder sirkular, sementara profil kecepatan diukur menggunakan pitot static tube yang terletak di belakang silinder sirkular. Pada penelitian eksperimental ini diperoleh reduksi koefisien drag pressure (CDP) paling besar terjadi pada silinder sirkular dengan penambahan bodi pengganggu berupa airfoil NACA 0024 pada variasi jarak longitudinal (S/D) = 1,6 sebesar 16,3%. Kemudian didapatkan pula reduksi koefisien drag pressure (CDP) paling rendah yaitu terjadi pada silinder sirkular dengan bodi pengganggu airfoil NACA 0012 dengan variasi jarak longitudinal (S/D) = 2,8 sebesar 1,2%. Berdasarkan grafik distribusi profil kecepatan dibelakang silinder sirkular didapatkan bahwa defisit momentum paling kecil terjadi pada konfigurasi jarak (S/D) = 1,6 dan NACA 0024. Sedangkan pada jarak (S/D) = 2,8 dan NACA 0012 menunjukkan defisit momentum paling besar. Semakin besar defisit momentum yang dihasilkan maka semakin besar wake yang terbentuk sehingga gaya drag yang terjadi pada silinder sirkular semakin besar, begitu juga sebaliknya.
===============================================================================================================================
In the field of engineering, particularly in fluid mechanics, calculations on the flow through a channel are often conducted, such as predicting the characteristics of the flow that occurs when passing through a channel. A circular cylinder is one of the most used geometrical shapes of a bluff body, which generates a large drag force due to the early formation of separation, resulting in a larger wake. The faster the separation of the flow occurs, the larger the wake area becomes. The magnitude of the drag force greatly affects the efficiency of work. Therefore, one way to reduce drag force is by manipulating the flow field. One method of manipulating the flow field is by using passive flow control. This research discusses the effect of adding an airfoil disturbance body in front of a circular cylinder. This research was conducted experimentally on a circular cylinder (D = 36 mm) with an airfoil disturbance body (NACA 0012, NACA 0018, NACA 0024) at an angle of attack of 5° placed in front of the circular cylinder in a sub-sonic wind tunnel with dimensions (h = 200 mm, z = 200 mm, x = 2000 mm), which was tested with variations in the S/D distance ratio of 1.6; 2.0; 2.4; 2.8. In this research, the pressure was measured using pressure taps installed on the surface of the circular cylinder, while the velocity profile was measured using a pitot static tube located behind the circular cylinder. In this experimental study, it was obtained that the largest reduction in drag pressure coefficient (CDP) occurred in a circular cylinder with an inlet disturbance body in the form of a NACA 0024 airfoil at a longitudinal distance variation (S/D) = 1.6 by 16.3%. Then the lowest drag pressure coefficient (CDP) reduction is obtained, which occurs in a circular cylinder with an inlet disturbance body in the form of a NACA 0012 airfoil with a longitudinal distance variation (S/D) = 2.8 by 1.2%. Based on the velocity profile distribution graph behind the circular cylinder, it is found that the smallest momentum deficit occurs in the configuration of distance (S/D) = 1.6 and NACA 0024. While at (S/D) = 2.8 and NACA 0012 shows the largest momentum deficit. The greater the momentum deficit produced, the greater the wake formed so that the drag force that occurs on the circular cylinder is greater, and vice versa.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Bluff Body, Passive Flow Control, Drag Force, Wake
Subjects:	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:	Muhammad Naufal Reiza
Date Deposited:	05 Sep 2023 03:07
Last Modified:	05 Sep 2023 03:07
URI:	http://repository.its.ac.id/id/eprint/102797

Actions (login required)

View Item