The model was initially developed by Gross&Harris and Gormont, the basic idea is as follows:
The onset of dynamic stall is assumed to occur at
where  is the critical AoA of dynamic stall,  is static stall AoA and  is given by
where  is the time derivative of AoA,  is the blade chord, and  is the free-stream velocity. The  function is empirical, depends on geometry and Mach number and is different for lift and pitching moment.
The airloads coefficients are constructed from static data using an equivalent angle of attack  derived from Theodorsen's theory at the appropriate reduced frequency of the forcing and a reference angle  as follows:
, , , where  is the center point of rotation.
A comprehensive analysis of a helicopter rotor using this model is presented in the reference.