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Help needed with Aerofoil Design

  1. Apr 27, 2012 #1
    Apologies if this isn't in the right place

    I am trying to design a controllable aerofoil to give different values of lift and drag for a race car. It will also be used as a brake. it will rotate to give different angles of attack. as a brake it was originally designed to be perpendicular to the air flow

    I've worked out that, under braking the required drag force, assuming no downforce is 1046.4N and using the formula Fd=1/2v^2CdA where,

    Fd=1046.4N
    ρ= air at 25C = 1.1839Kg/m^3
    v= 27.3647m/s
    Cd = 2 (flat plate)
    and A is to be found

    A is given to be 1.18m^2 which is quite small and given that the intended wing span was to be 750mm this gives a tiny width of the wing.

    Are there any simple formulae using just these values to give the drag and downforce for certain aerofoils at certain angles of attack?

    Any help would be greatly appreciated

    Thanks
    D
     
    Last edited: Apr 27, 2012
  2. jcsd
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