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September 17, 2006, 04:20
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3D,analysis of NACA-0012,with WINGLET & non.
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Guest
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I need an analysys of NACA 0012 Airfoil(chord=1 unit & SPAN =8 x chord) one time without any winglet.other time with very thin winglet(NACA 0012) installed at 90,115,125,135,145 degree ANGLE to outbord(for example the shape is for 135 deg = _____________/ & for 90 deg = _____________| ). (span of winglet is 0.5 chord of wing).upstrem velocity is 200 m/s. the output needed Cl-Cd at angle of attack between 0 to 10 degree & contour of velocity & pressure change in 3D & 2D. I need to ploting result.... PLEASE HELP ME,I have only 2 days time. PLEASE,PLEASE WITH BEST REGARDS THANK YOU
17 sep 2006 |
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September 17, 2006, 10:59
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Re: 3D,analysis of NACA-0012,with WINGLET & non.
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1 - open the software 2 - build the mesh 3 - define boundary conditions 4 - run the simulation 5 - post-process 6 - you've done your own job for once
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September 17, 2006, 15:56
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Re: 3D,analysis of NACA-0012,with WINGLET & non.
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No i have not any time I need a solved problem.!!! if you can help me please help,...... I have not any software for solving this problem. I don't how work with this software? PLEASE help me? THANK YOU
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Linear Mode
