lions48 said:
From the PDF file: "There is a lower pressure of air on the top of the airfoil because the air takes longer to get to the same point."
This is called "equal transit theory", and it's not true. The air disturbed by a wing is displaced. Molecules that were once adjacent to each other, and then separated into flow above and below a wing remain separated.
The math part of the PDF document is correct, except that coefficient of lift and coefficient of drag are not constants, but instead somewhat dependent on the other parameters in the equation, such as wing chord length and relative velocity between wing and air. The velocity times wing chord length (times a constant) equals something called Reynolds number, which is often used as a basis for plotting the cofficient of lift and/or drag versus angle of attack (such graphs are sometmes called polars).
Although an explanation of lift and drag aren't needed for your specific assignment with the wind tunnel, here is a link to one of many articles that gives a simplified explantion of lift:
http://www.avweb.com/news/airman/183261-1.html
The more complex analysis invovles something called Navier Stokes equations, which normally can't be directly solved, but there are programs that use Navier Stokes as a basis to produce those charts called "polars" given airfoil shape, size, and velocity of the air, where the charts plot coefficient of lift and/or drag versus angle of attack (and/or lift versus drag ...).
You didn't mention if you're allowed to try several different airfoil shapes in the wind tunnel to see which gives the best results.