In the takeoff roll, I'm pretty sure planes produce some lift before rotation, but how much? Is it insignificant compared to post-rotation, or is it large compared to the post-rotation lift?
Check out this plot (taken from wikipedia), of the lift coefficient against angle of attack. During takeoff roll, lift will be increasing due to the speed increasing, however not enough (in general) for the plane to achieve takeoff without rotation.
Once rotation starts, the lift increases dramatically, for (a very rough) example, consider a plane on takeoff roll, then rotating to 15 degrees angle of attack. By looking at the lift/AoA plot, we can see that the lift coefficient increases from roughly 0.55 to 1.7, giving roughly 3 times as much lift as before rotation.
Rotation increases the angle of attack, and as a result, the lift force also increases. However, there are aircraft that do take off with very little angle of attack change (maybe a couple of degrees, as in the case of UAVs). For those aircraft the lift force before rotation can be 60-70 % of the weight of the aircraft. Remember, for take off to happen, the lift force must be at least equal to the take off weight.
One more parameter is, of course, the airspeed. The lift increases with the square of the airspeed. And at the time of rotation, comparing just before and just after liftoff, the lift generated are quite close to each other, depending on the change of alpha (angle of attack). At a stationary airplane, with no headwind, there is no lift (ignore engine flow).
To sum up, during the ground roll, from standby to rotation, the lift increases from zero to a large fraction of the weight. The fraction depends on the type and design of the aircraft, but cannot be equal to the weight.