Predicting lift on an Aerofoil with varying Angles of Attack

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The discussion focuses on the challenges of predicting lift on an aerofoil concerning varying angles of attack for a school experiment. The formula for lift, L = (1/2) d v² s CL, is acknowledged, but the participant seeks a lift coefficient formula that incorporates the angle of attack. Tools like XFOIL and JavaFoil are suggested for generating airfoil performance data. The participant also questions whether to consider stall in their calculations. Accurate modeling of lift and stall is emphasized as complex but essential for reliable results.
Tom 77
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
 
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Tom 77 said:
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.
https://en.wikipedia.org/wiki/Airfoil#Thin_airfoil_theory
 
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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
 
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