In this video, Nick discusses Lift.

In the most basic terms, Lift equals Dynamic Pressure multiplied by the Surface Area multiplied by the Lift Coefficient. Which also equals the load factor of the airplane is under, times the weight of the airplane. So lift is qSCL. Q is dynamic pressure, and the way engineers do it, in the most simplistic terms, is V squared over 295, and that’s equivalent airspeed in knots. This would be your wing reference area like on the Citation Jet it which is about 240.  And CL is lift generated at that time.  This has to also equal  NzW. CL is a non-dimensional coefficient.