XFoil is an example of software developed by Dr. Mark Drela of MIT.
http://web.mit.edu/drela/Public/web/xfoil/
you can work "Backwards" with this application stipulating pressure coefficients and outputting the section geometry...
as well as taking existing sections that might be close and...
yes.. keep the units straight...
the above formula is good for approximations...
but keep in mind.. the fuselage can create lift.. as well as the tail.. (Lift downward actually)...
so the sum of all lifting forces need to be considered...
as well as a particular wings Cl max...
if in the assignment you were not given specific goals... you could have conjured'em up yourself...
but a wing is a big deal and in the real world.. a wing design has 10 man*years of trade studies!
example... a thicker wing... structurally more efficient... drag penalty... where is the sweet spot?
usually called "Trim Drag"...
the sweet spot is for the CG to be at the neutral point so that tail is making no lift.. but providing pitch stability through an active system (SAS)
a sailplane is a good example... the CG is just enough fwd of the neutral point that a pilot can control the...
basically... thrust is a function of Mass and Acceleration...
the energy used is a function of mass and Acceleration^2
so maximizing the mass of air accelerated and minimizing the Delta-V is more efficient...
ever heard "Pressure Recovery"...
a duct with 98% Pressure recovery is nice...
an "S" duct with a 96% recovery (a length-diameter ratio of say 4'ish) is good too...
if all is perfect... you will loose total pressure from boundary layer effects...
incorporate diffusion and see how messy it...