keendog wrote: "Most non-aerobatic aircraft have, for various aerodynamic reasons, cambered wings."
Just to amplify that a little, the asymmetry of a wing is by no means essential in producing lift.
A symmetric aerofoil produces plenty of lift as you give it an angle of attack. Typically you get a lift coefficient (just think of it a a measure of the lift) of about 0.1 per degree of AOA. So the lift coefficient is +0.5 at 5 degrees up, zero at zero degrees and -0.5 (pushing down) at 5 degrees down.
If you camber the aerofoil, you offset the angle at which you get zero lift. So you might get +0.5 at 3 degrees up, +0.2 at 0 degrees AOA, zero at 2 degrees down and -0.5 (pushing down) at 7 degrees down.
Why bother to camber the aerofoil at all? Why not just give all aeroplanes symmetric aerofoils and get them to fly at slightly higher AOAs? Well the minimum drag tends to occur close to zero degrees AOA: so you can get a better lift/drag ratio by cambering the aerofoil so its AOA is zero (or close) at the typical lift coefficient you want it to be flying at most of the time.