I am suggesting what tdracer wrote earlier: - So that's a long way of saying that 'no, the controllability analysis for a deployed reverser was not done
For Boeing that seems..
Ok that's past tense. I am looking at today for the specific malfunction the OP set forth at V1 speed with all engines operating.
The N1 decay rate is known (FADEC chop), the efflux is known, the effect on the wing devices can be modeled along with the lift vs aircraft speed with variable rudder inputs.
What seems to be in question is the pilot inputs for braking, rudder or aerilons vs altitude