Most compressors are designed around 0.5 Degree of reaction ratio, meaning half of the static enthalpy rise (and thus pressure) occured in the rotor and half at the stator. The stages can be esigned with 0 degree of reaction, meaning no pressure rise occurs in the rotor, (rotor blades are thus of an "Impulse" type). They can alternately be designed with a factor of 1, meaning all pressure rises occur in the rotor. thus the stator is of the "impulse" type.
In reality, the degree of reaction varies along the length of the blade, ie the level of convergence/divergence of the stator varies. This is in order to take into account of supersonic flow patterns (remember, supersonic flow accelerates in a diverging passageway). hope that helps!