Aerodynamic Study of Air Flow over A Curved Fin Rocket

Md Nizam Dahalan; Ahmad Fitri Suni; Iskandar Shah Ishak; Nik Ahmad Ridhwan Nik Mohd; Shabudin Mat

Authors

Md Nizam Dahalan nizamdahlan@utm.my
Ahmad Fitri Suni Department of Aeronautical, Automotive and Ocean Engineering, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
Iskandar Shah Ishak Department of Aeronautical, Automotive and Ocean Engineering, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
Nik Ahmad Ridhwan Nik Mohd Department of Aeronautical, Automotive and Ocean Engineering, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
Shabudin Mat Department of Aeronautical, Automotive and Ocean Engineering, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia

Keywords:

Curved fin rocket, numerical simulation , semi-empirical method , aerodynamic characteristics regime

Abstract

This paper summarizes a study of the aerodynamic characteristics of a curved fin rocket. The study was conducted with the use of semi-empirical method and numerical simulation. The semi-empirical method was implemented with USAF DATCOM as a reference. The ANSYS Fluent was used for the numerical simulation. The curved fin rocket configuration included a conical nose, a cylindrical body, and four curved fins attached symmetrically at the aft body of the rocket. The semi-empirical method and numerical simulations were undertaken at various Mach numbers, which were 0.15, 0.4, 0.6 and 0.8 for subsonic speed. For supersonic speed, the Mach numbers were 1.2, 1.4 and 2.0. The angle of attack varied from 0 ̊ to 25 ̊ for each speed, at 5 ̊ increments. The compared results included those attained from wind tunnel testing, USAF DATCOM, numerical simulation, and those results gathered from previous researchers. According to the results, each method resulted in the same trend, and followed typical rocket aerodynamic characteristic trends.

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Author Biography

Md Nizam Dahalan, nizamdahlan@utm.my

Department of Aeronautical, Automotive and Ocean Engineering, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia ARTICLE INFO ABSTRACT Article history: Received 11 December 2017 Received in revised form 25 December 2017 Accepted 28 December 2017 Available online 30 December 2017This paper summarizes a study of the aerodynamic characteristics of a curved fin rocket. The study was conducted with the use of semi-empirical method and numerical simulation. The semi-empirical method was implemented with USAF DATCOM as a reference. The ANSYS Fluent was used for the numerical simulation. The curved fin rocket configuration included a conical nose, a cylindrical body, and four curved fins attached symmetrically at the aft body of the rocket. The semi-empirical method and numerical simulations were undertaken at various Mach numbers, which were 0.15, 0.4, 0.6 and 0.8 for subsonic speed. For supersonic speed, the Mach numbers were 1.2, 1.4 and 2.0. The angle of attack varied from 0 ̊ to 25 ̊ for each speed, at 5 ̊ increments. The compared results included those attained from wind tunnel testing, USAF DATCOM, numerical simulation, and those results gathered from previous researchers. According to the results, each method resulted in the same trend, and followed typical rocket aerodynamic characteristic trends. Keywords:Curved fin rocket, numerical simulation, semi-empirical method, aerodynamic characteristics regime Copyright © 2017 PENERBIT AKADEMIA BARU - All rights reserved 1. Introduction The rocket is one of the greatest inventions developed by human beings. The first rocket was created in China in 1200, and its first use was as fireworks during Chinese New Year celebrations [1]. Currently rockets are being utilised in various fields, including in space exploration, and by military force. Their role in space exploration can be observed clearly when modern nations such as Russia, the US, India, France and China, use rockets as the basis of their spacecraft. Rockets are used to transport humans to outer space, possessing sufficient thrust to overcome the earth’s gravitational force. The Soyuz and Saturn rockets are prominent examples. Rockets act as the preliminary booster for transporting the space shuttle, and satellites, into outer space. ∗Corresponding author. E-mail address: nizamdahlan@utm.my (Md Nizam Dahalan)PenerbitAkademia BaruOpen Access