Eh, I'll throw you a bone. The shape of the airfoil, camber, is only one factor in lift. Trying to explain lift only with Bernoulli's equation is overly simplistic. A high lift wing is going to have that text book curved top, flat bottom, since it is designed to be efficient while flying upright. As others have mentioned, aerobatic wings tend to be symmetrical. So how do they generate lift with a symmetric wing? Angle of attack. A high lift wing could fly inverted, but it won't be very efficient, requiring a greater angle of attack than if it were upright. Maybe this inverted angle of attack required exceeds the critical AOA, resulting in stall and a plane that cannot maintain level inverted, or maybe not. The T6A at ~220 knots level has a pitch roughly at 0° to maintain level. Inverted level is roughly 15° nose up, which is held there with forward stick pressure. Also, more AOA means more induced drag, requiring more thrust to maintain level flight. Don't think of the horizontal stab as providing lift for inverted flight though, think of it as a mechanism to set your AOA regardless of whether you are upright or inverted. For a symmetric wing, the level AOA upright vs inverted would be very similar. Lift is almost solely based on AOA in these wings. There's your 2 cent overview of inverted flight. Aerodynamics for Naval Aviators is a good read if you want to nerd out on aerodynamics, or you can just push the "I believe" button. Now for some homework... 1) how do some airplanes fly knife edge (90° bank) and still maintain level flight? 2) is flying level inverted the same as passing through inverted in a loop or barrel roll? Or is there another force to consider?