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Determine Lift

  1. Oct 21, 2007 #1
    1. The problem statement, all variables and given/known data
    I have recorded raw pressures for from a wind tunnel for a NACA 0012 airfoil with 30 surface pressure taps.

    I have computed Reynolds Number for 3 angles of attack.

    I have computed the Pressure Coeff. for each pressure and graphed them verses the non-dimensionalized tap locations.
    This is where I am stuck:
    Numerically integrate the pressure distribution ( trapezoidal rule) to estimate lift.

    2. Relevant equations


    [tex] F_{A} = \int_{x=0}^{c}(p_{u})(\frac{dy}{dx})_{u}+(p_{l})(\frac{dy}{dx})_{l}dx[/tex]

    [tex] L = F_{N}cos(\alpha)-F_{A}sin(\alpha)[/tex]

    F_{A} is axial force and F_{N} is normal force
    Pu is upper surface pressure, Pl is lower surface.

    3. The attempt at a solution

    I am completely stuck.
  2. jcsd
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