The question is:

An Aeroplane weighing 250000N has a wing loading of 3125Nm^-2 and its Drag equation is given by

CD = 0.016 + 0.04CL^2

Calculate the minium thrust required for straight and level flight.

That is just the first part of a very long question, I think I can do the rest of it if I can get this first part done, so far all I have is the area of the wing is 80m^2.

Any help would be great. Not looking for a specific answer, just someone to suggest a forumla or something I might have missed. Used everything I can find in my books and on the internet, but obviously, I've missed something otherwise I would have done it.

Thanks