naca section

[jejojoy]

hi
can anyone help me in obtaining the lift and drag characteristics of naca 0012 section for a reynolds number of abt 3 * 10^8..wat is the drag coefficient at zero angle of attack for the above mentioned reynolds number

[Figgy]

Have you tried X-Foil?
http://web.mit.edu/drela/Public/web/xfoil/
It's a good program, it might help you out with this kind of stuff.

I see from your other posts you have had a hard time with X-Foil.
Have you tried JavaFoil?
http://www.mh-aerotools.de/airfoils/javafoil.htm

[Raggi_Thor]

I searched google, this may be useful,
http://www.cyberiad.net/library/airf...ta/n0012cd.htm,

-------------------------------- REYNOLDS NUMBER -----------------------
ALPHA 160000 360000 700000 1000000 2000000 5000000
------------------------------------------------------------------------
0 0.0103 0.0079 0.0067 0.0065 0.0064 0.0064
1 0.0104 0.0080 0.0068 0.0066 0.0064 0.0064
2 0.0108 0.0084 0.0070 0.0068 0.0066 0.0066
3 0.0114 0.0089 0.0075 0.0071 0.0069 0.0068
4 0.0124 0.0098 0.0083 0.0078 0.0073 0.0072
5 0.0140 0.0113 0.0097 0.0091 0.0081 0.0076

[Jimbo1490]

The free version of Profili does so much more than X-foil while using the same profile generating engine. Just download it. If you want to print, plot or save in any pratical way, you will need to pay the very modest $10 licence fee.

Jimbo