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B Predicting lift on an Aerofoil with varying Angles of Attack

  1. Jul 20, 2017 #1
    I am conducting a school based EEI and have found issues in predicting lift on an aerofoil with respect to angle of attack.I understand the formula for lift is L = (1/2) d v2 s CL. I also understand there are many confusing variations to the calculation for the lift coefficient but i am yet to find one that takes the angle of attack into account.

    The idea of the experiment is to find the optimum angle of attack to velocity ratio in a wind tunnel acting on a cambered aerofoil and i would like to predict the lift per angle prior to testing, then to reveal the differences and use results for error. Is there a formula i can use to calculate the predicted lift of an Aerofoil which incorporates the angle of attack. I really appreciate any advice or support. Thanks
     
  2. jcsd
  3. Jul 20, 2017 #2

    A.T.

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    https://en.wikipedia.org/wiki/Airfoil#Thin_airfoil_theory
     
  4. Jul 20, 2017 #3

    rcgldr

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    Getting a reasonably accurate model is fairly complicated. This is an example library / program that generates data about airfoil performance:

    http://web.mit.edu/drela/Public/web/xfoil
     
  5. Jul 20, 2017 #4

    A.T.

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  6. Jul 20, 2017 #5
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