This is a really interesting one.
All wings will produce SOME lift at zero AOA. Look at a typical lift curve slope, you have peak CL at something like 1.0 or so at an AOA of 15 degrees (just before the stall), and a CL of (in this example) about 0.1 at 0 degrees AOA. I don't have enough posts to post a link, so google is your friend!
Typical cruise AOA would be about 3-4 degrees, for a CL of, say, 0.4.
If we go to our lift equation, we can see that lift = 0.5 x CL x rho x S x V^2. Double the velocity, and you can quarter the CL for the same lift.
So if you are, say, in steady level flight at 4 degrees AOA, CL of 0.4 at 100 KIAS, then doubling your airspeed to 200 KIAS requires one quarter the CL, i.e. 0.1.
You are in steady level flight at 0 AOA with a CL of 0.1. Any faster, and you will be in steady level flight, with a positive CL, and a slightly negative AOA.
Magic!