Study of vortex trap on low aspect ratio wing with NACA 0015 cross section

Abd.Y.Gandouz, Suliman (2011) Study of vortex trap on low aspect ratio wing with NACA 0015 cross section. Masters thesis, Universiti Tun Hussein Onn Malaysia.

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Abstract

The purpose of this project is to apply a numerical procedure for flow analysis over a low wing aspect ratio with and without a groove by Gambit and FLUENT software. Gambit software used for generating mesh over flow domain surrounding the wing, while FLUENT as the flow solver software. The wing has a rectangular form with its airfoil cross section is NACA 0015 and wing aspect ratio equal to 0.66. Numerical procedure starts with creating wing plan form by used solid work software. The data geometry then transported to Gambit in order to allow mesh flow domain can be created. This had been done on two wing models. The first wing model is considered as the wings with clean airfoil section while the second one as the wing with its airfoil with groove. The first wing model is called as a baseline model. Both models then solved by use of Fluent software at the free stream velocity at 40 dsec and Reynolds number RL=400000 for different angle of attacks at a = o', 5', 15', 25' and 40'. The result shows that in term of overall aerodynamics characteristics, namely the lift coefficients CL, had been found relatively low compared to the typical value of lift coefficient of the airfoil. This result represents a reasonable result since typical value of lift coefficient for a low aspect ratio is very low compared with the lift coefficient of its airfoil. The consequence of low aspect ratio made the wing able to delay the presence of flow separation although setting angle of attack is high. As result the effect groove in this present work in term of delaying the flow separation is so significant. Wing without groove still able to produce lift forces as it happen on the wing with groove. The comparison result flow phenomena between those two wing models are discussed. The flow analysis for the same wing model but with high aspect ratio is suggested for the future work in order to give a better assessment for the influence of groove.

Item Type:Thesis (Masters)
Subjects:T Technology > T Technology (General)
ID Code:2427
Deposited By:Normajihan Abd. Rahman
Deposited On:04 Apr 2012 08:59
Last Modified:04 Apr 2012 08:59

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