The max gee occurs at 15 deg AOA or so if going fast enuf, then the gee decreases to approx 1 gee at 25 deg AOA, regardless of how much you are pulling on the pole.
The 25 deg AOA limiter was intended to allow a super turn rate without bleeding off a lot of energy. Further, the pilot did not have to worry about pulling too hard at slow speed, as the jet would give you its best, and you could concentrate on tactics, looking around, etc.
The most important thing to remember about AOA is that the amount of lift the aircraft is producing is roughly proportional to the angle of attack times the square of your airspeed. What this means is simple - if you are flying slow, you will need to maintain a higher angle of attack in order to keep the airplane in level flight. If you maintain a constant angle of attack while slowing down, the aircraft will begin to descend. Likewise, if you maintain an angle of attack while speeding up, the aircraft will begin to climb.
All wings have what is known as a "critical angle of attack". If the critical AOA is exceeded, the aircraft will "stall" - the airflow will separate from the wing and become turbulent, preventing the wing from producing lift, and the aircraft will begin to fall (as in "fall like a rock", not "descend like an airplane"). The ONLY way to recover from a stall is to reduce the angle of attack by increasing power and pushing the aircraft's nose down. If you pull back on the stick or allow the stall to continue, the angle of attack will continue to increase, deepening the stall and making it more difficult to recover. Eventually, you will end up in a "deep stall" where the aircraft is essentially falling straight down. These are extremely difficult to recover from.
The flow visualization of Sukhoi Su-30MKI like-model using GAMA water tunnel has been conducted to investigate the vortex dynamics on canard and main wing. This work aimed to observe the aerodynamic force and the vortex-dynamic phenomenon. The water tunnel is an effective visualization method to determine the vortex-dynamic phenomenon which was used in this research. The usage of water tunnel would make it easier to reveal the phenomenon that occurred. The results of GAMA water tunnel experiment showed the aerodynamic force and vortex dynamics phenomenon on the model of Su-30MKI aircraft. The increasing of lift force was started from a small angle of attack (AoA) to a maximum value at an angle of 45 degrees. The maximum lift value on the test using GAMA water tunnel was about 1.38. The vortex dynamics have been particularized using observation of vortex core formation and vortex breakdown location. The higher of AoA caused unstable vortex core flow so that the vortex breakdown location would lead to leading edge.
Source :
file:///C:/Users/panda/Downloads/Vortex_Dynamics_Study_of_the_Canard_Deflection_Ang.pdf
