I'm designing an aerobatic aircraft similar to EXTRA 330SC. I would like to know about stability: lateral and longitudinal, static and dynamic. I read that aerobatic aircraft have neutral static stability. Some books relate Cm to AoA. Others relate Cm to CL. Please detail more about this or provide some bibliography.
If you are serious about designing an airplane that will one day fly and certify, you should, to the very least, read up Raymer, Aircraft Design: A Conceptual Approach. It has a chapter on stability & control, and would be a good introduction to the lingos.
More in depth coverage can be found in Etkins, Dynamics of Flight. It's pretty much the bible for S&C engineers.
Once you feel like you have the theory down, design guidelines for conceptual design (even preliminary design) can be found in Roskam, Airplane Design.
Since design goes hand-in-hand with certification requirements, a knowledge of 14CFR Part 23 and AC 23-8C wouldn't hurt.
The farther forward the center of mass is from the neutral point, the more stable the airplane is in pitch. When the two coincide, the airplane becomes pitch-unstable. When center of mass is behind, human reflexes are insufficient to maintain controlled flight.
As far as designing goes, center of mass and AoA are different beasts. Center of mass stays roughly the same, while AoA (especially in aerobatics) changes greatly and quickly.
Others here have explained further.