Originally Posted by HN39
For a given airplane configuration, weight, Mach, and 1g, c_L is inversely proportional to ambient pressure, so it increases with altitude. With increasing AoA the shape of the pressure distribution over the chord changes, in many cases it becomes more 'peaky'.
Give the relationship you have "simplified", and we can discuss it. This formulation is too vague for me to see what you are trying to get at.
For example, I can't see how c_L is dependent on weight. For c_L has a two-dimensional definition, and it is the same whether your wing is one meter span or one hundred, whereas weight is for the entire three-dimensional airplane.
PBL