Mohamed Yusop, Fatimah (2016) *The development of Euler solver based code for external aerodynamics flow.* PhD thesis, Universiti Tun Hussein Onn Malaysia.

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## Abstract

Tinoco (2009) estimated that direct solution to the Navier-Stokes equation in line with the progress in the development of computing power and the algorithm in solving the non-linear partial differential equation can be made in the next 65 years from now [1]. Realizing the highly demanding computer power, the way to solve the flow problems is by adopting some sort of simplification of Navier-Stokes equation according to physical flow phenomena consideration. Such approach gives, for instance, to the case of flow past through a streamline body at high and at low Reynolds number to moderate angle of attack, the Navier-Stokes equation can be simplified by ignoring viscous effects resulting a new governing equation of fluid motion named Euler equation. However, this equation is still belongs to the class of non-linear partial differential equation, while result in numerical approach is required. The main features of compressible flow are the presence of discontinuity flow phenomena due to shock wave and a contact surface. Such flow phenomenon is always found if the flow in transonic or supersonic flow regimes. As a result, all the aircrafts designed to fly at transonic or supersonic speed will face such flow phenomenon. It is therefore, all numerical schemes designed to be a tool for aerodynamics analysis or aerodynamics design tool must be able to predict the presence of such discontinuity flow phenomena accurately. The present work focused on the development of computational fluid dynamics (CFD) aerodynamics analysis tool by solving the compressible Euler equation through a finite difference method (FDM) as well as a finite volume method (FVM). The FDM used the method developed based on Davis-Yee TVD scheme. While that, the FVM was developed by using Roe scheme. In view of TVD scheme, there were various methods in involving a limiter functions. The use of various limiter functions as part of the development of CFD software is also carried out in the present work. To validate the developed software, these two types of CFD code are applied for solving the high Mach number flow past through airfoil. The airfoils are (1) the conventional airfoil NACA0012 and (2) the supercritical airfoil NASA SC (2)-0714. Then, the comparison is made by comparing their result with the ANYSYS-FLUENT software as well as with the experimental result as stated in the literature. Through results comparison for these two different airfoils operated at various angles of attack, it had been found that the developed CFD code based on Davis-Yee TVD scheme are able to produce the result close to the experimental result compared with the result produced by ANSYSFLUENT software or the code developed based on Roe finite volume scheme.

Item Type: | Thesis (PhD) |
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Subjects: | T Technology > TJ Mechanical engineering and machinery > TJ266-267 Turbines. Turbomachines (General) |

ID Code: | 9224 |

Deposited By: | Mr. Mohammad Shaifulrip Ithnin |

Deposited On: | 02 Aug 2017 16:40 |

Last Modified: | 02 Aug 2017 16:40 |

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