Thank you so much! I can’t wait to pursue rocket engineering further and there
is still so much for me to learn,
Charlie.
On 13 Aug 2021, at 01:12, roxanna Mason <rocketmaster.ken@xxxxxxxxx> wrote:
That explains it Charlie, the heat flux will be less severe than
traditionally higher Pc so cooling will be less challenging. Just keep the
coolant velocity in the nozzle area higher than the chamber. Steel has
considerably lower thermal conductivity than copper so keep that in mind. I
built a similar engine in my high school machine shop as a sophomore. Throat
diameter was 1/2", GOx/Gasoline, water cooled. The sight of my first pea size
shock diamonds was so exeliating I was permanently addicted to rocketerty. I
got a condition called thrust fever, bigger and bigger rocket engines became
my obsesion.
Good luck,
Ken
On Thu, Aug 12, 2021 at 11:02 AM Charlie Jackson
<charliejackson8629@xxxxxxxxx> wrote:
The chamber pressure is 150psi
From: roxanna Mason
Sent: 12 August 2021 18:38
To: arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Combustion Chamber drawing
What's your chamber pressure? The nozzle area ratio,epsilon, is only 2.45
assuming expansion to SL. Looks like you read the China Lake book on
building small water cooled liquid fuel rocket engines.
Ken
On Thu, Aug 12, 2021 at 10:13 AM Charlie Jackson
<charliejackson8629@xxxxxxxxx> wrote:
Hello everyone,
May I get some feedback on my technical drawing for a mild steel combustion
chamber before I send it to the machinist please? Have I over/under
toleranced any dimensions? And is there anything I can add to make the
design cheaper or more concise? This is my first time making an engineering
drawing so apologies if I have missed anything.
Many thanks, Charlie
