Hello PpruNe
a graphical illustration of coef. of yawing moment (N) Cn vs. the EAS where Cn=N/qSb: would demonstate that Vmc occurs where maximum yawing coef. with maximum rudder imput is equal to to the Yawing moment induced by the thrust asymmetry and the total is = 0
this is a function independent of weight, or altitude simply EAS
Vmc is the lowest Speed where Cn (due to max rudder deflection)=Cn [due to thrust asymmetry]. since the decision speed V1 will occur at a higher EAS than Vmc where there is excess yawing force available to the rudder at the higher EAS negating the criticality of the asymmetry that is why Vmc is critical at light weight
A slight bank is required to stabilize the flight path but sideslips as is often though is not zero at Vmc
