And now, I will talk about what I have done so far.
First, you have FL= [latex]\int_{A}[/latex] np dA. To get the coefficient of lift, then you must divide this by [latex]qA[/latex]. This gives you CL=[latex]\int_{A}[/latex] [latex]{np}/{qA}[/latex] [latex]{ dA}[/latex], which is equal to [latex]\int_{A}[/latex] [latex]{n}/{q}[/latex] [latex]{ dp}[/latex]
Using integration by parts, you find that:
latex]\int_{A}[/latex] [latex]{n}/{q}[/latex] [latex]{ dp}[/latex] = nΔp/q - [latex]\int_{A}[/latex] p/q dn
For the first term, then it is change in pressure because it is evaluated among the top and bottom areas, and so, you get the change in pressure. I just need to find what this change would be.
For the second term, then I need to make this integral in terms of A, so I changed dn to dA dn/dA, and this makes it an integral with respect to A. Now, I need to find dn/dA, along with the change in pressure.