Load factor is the number of "g" the aircraft is experiencing. Standard rate of g is 9.81m/s^2.
0.98g is almost 1g, ie normal conditions. When aircraft are carrying out flight testing, the pilot tries to keep the aircraft at 1g through the deceleration phase, to reach the stall. In normal circumstances, human error is such that just before the stall, the pilot might pull back ever so slightly on the stick, increasing the load factor slightly, so it is infact interpolated.
At the stall, the aircraft reaches CLmax (fnnar fnnar), and with a load factor, this will increase the stall speed.
Wing loading is different. In wing designer terms, it is W/S or weight per unit area of wing (includes the wing area sheilded by the fuselage). In pilot terms, loading and ng (n being the number of g) are the same thing.
Dont shoot me down in flames guys, its been a while
