I was wondering about something I thought the insight of this group could
help me with.
For a *small* liquid propellant rocket engine running Kerosene and LOX,
what would be the consequences of a characteristic length of around only 12
inches?
Could small attitude control thrusters run with an L* as low as that under
reasonable operating conditions (i.e. combustion completion issues, etc)?
I'm wondering since someone here mentioned the Rocketdyne LR-101 engine
uses an L* of 20", yet the texts I've found have RP-1 and LOX L* values
much higher than that, and that made me wonder whether the characteristic
length could be taken even smaller for amateur engines.