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thatjazzdude89

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- TL;DR Summary
- How does the geometric shape of an airfoil effect 2D lift coefficient?

I’m aware that this is a simple question to a very complex question. However, I’m curious as to how to calculate a lift coefficient simply using a 2 dimensional equation or a series of 2 dimensional equations, such as the NACA equations. I’m somewhat familiar with the lift line theory, but to be honest it seems very complex and I am not aware of a simple and practical way to apply it. By this I mean; I would like to take the NACA or 2D airfoil equations and plug them into another set of equations to arrive at a usable result for overall wing design. I apologize for any ignorance on my part; I’m a community college graduate who enjoys designing RC aircraft as a hobby, so I have not taken any aerodynamics classes or training. Thanks for any assistance.