naca section

Discussion in 'Propulsion' started by jejojoy, Oct 9, 2006.

  1. jejojoy
    Joined: Jun 2006
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    Location: india

    jejojoy Junior Member

    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
     
    jejojoy, Oct 9, 2006
    #1
  2. Figgy
    Joined: Feb 2006
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    Location: TN

    Figgy Senior Member

    Figgy, Oct 9, 2006
    #2
  3. Raggi_Thor
    Joined: Jan 2004
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    Location: Trondheim, NORWAY

    Raggi_Thor Nav.arch/Designer/Builder

    I searched google, this may be useful,
    http://www.cyberiad.net/library/airfoils/foildata/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
     
    Raggi_Thor, Oct 9, 2006
    #3

  5. Jimbo1490
    Joined: Jun 2005
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    Location: Orlando, FL

    Jimbo1490 Senior Member

    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
     
    Jimbo1490, Oct 9, 2006
    #4
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