3D,analysis of NACA-0012,with WINGLET & non.
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. 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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