AOA for max lift
A related question is what percentage of maximum aerodynamic lift capability does the Airbus normal law allow the pilot to command? It is my understanding that alpha-max as chosen by the control law designers to be the maximum commandable AOA is actually lower than the AOA corresponding to Cl-max. Seems to me that this system leaves some lift capability on the table and does not allow the pilot to command max lift. Anyone who knows the details care to comment?