The development of Euler solver based code for external aerodynamics flow
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...
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| Format: | Thesis |
| Published: |
2016
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| Subjects: | |
| Online Access: | http://eprints.uthm.edu.my/9224/ http://eprints.uthm.edu.my/9224/1/Fatimah_Mohamed_Yusop.pdf |
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| Summary: | 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. |
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