Hi All - I’m in the early stages of designing a 500 lbf 350 psiaLOX/Kerosene
engine with a 1.1 inch throat diameter and I was wondering if Icould quickly
check my math regarding L*and chamber/throat contraction ratios. From
reviewing H&H, it seems to suggest that an appropriateL* value is in the range
of 40 to 50 inches for this propellant combination (table4-1). Further it goes
on to say that for an approximately 1 inch throat diameterthe contraction ratio
is roughly 5.5 and the chamber length is slightly below 5inches (from fig 4-9
and 4-10 respectively). Since I suspect that this is a similarly sized engine
tothose others have built I wanted to check quickly to see if others have
hadgood experience with those numbers? Please feel free to ask any additional
clarifyingquestions. Thanks as Always,Graham
