Airfoil aerodynamics analysis by using viscous-inviscid direct analysis

Che Mohd Husin, Mohd Faizal (2011) Airfoil aerodynamics analysis by using viscous-inviscid direct analysis. Masters thesis, Universiti Tun Hussein Onn Malaysia.

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Abstract

The main objective of this research is to develop computer code for airfoil aerodynamics analysis. The flow assumed to be incompressible and pass through a streamline body at relatively high Reynolds number. As result the flow domain around the airfoil can be divided into two regions, namely the flow region closed to the airfoil surface and the flow region relatively far away from the surface which the viscosity effects can be ignored. The first flow region is known as Boundary layer region while the second flow region is called as inviscid flow domain. The inviscid flow problem can be solved by use a Panel Method. While the boundary layer region can be solved by two approaches depended on the governing equation had been used to represent the flow behavior inside the boundary layer. For boundary layer analysis, the present work used the combined Thwaites - Head's method and Keller Box Method. As result two computer codes had been developed. The fmt computer code called as The Present Computer Code 1 is the computer code which consists of Panel Method and the combined Thwaites - Head's Method, while the second code called as The Present Computer Code 2 represents the combination between Panel Method and Keller Box Method. Both computer codes use a Michele method for predicting the transition point laminar to turbulent. Both computer code applied for several test case of airfoil at different angle of attack and compared with result provided by XFOIL Code. Their comparison results show encouraging result and for the Keller Box method may need exploration further more in order improve their accuracy in turbulent part.

Item Type:Thesis (Masters)
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics
ID Code:2414
Deposited By:Normajihan Abd. Rahman
Deposited On:02 Apr 2012 15:55
Last Modified:02 Apr 2012 15:55

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