>>11197720Nah, for something like the Castor 600 the nozzle throat diameter is ~1/4rd of the total body diameter.
We know the body has a diameter of 3710 cm so estimating (because I can't find numbers) we get a throat diameter of ~927cm.
Thing is rockets don't give a shit about the diameter of anything, cross sectional area is what matters to flow.
With a diameter of 927cm we have a area of 674,915 cm2 for the throat and with a diameter of 3710 cm for the body we get an area of 10,810,298 cm2.
Blowing out the whole nozzle including the convergence in this case would increase the area by ~16 fold leading to ~ 1/16th of the trust.
I have blown enough nozzles out of solid motors over the years to learn this the hard way.
>>11197726Just because they do it the hard way on the Shuttle doesn't mean solid fuel can't be cast quickly and cheaply, look at military applications to see their techniques. Sure you lose some ISP but when you go big enough that stops mattering so much.
