I'm trying to design a liquid fueled rocket engine, with copper walls cooled by kerosene.
While designing it, the following formula comes out:
Q = total heat transferred
q = average heat transfer rate
A = heat transfer area
w = coolant flow rate
c = specific heat of coolant
T = temperature of coolant leaving the engine
T(i) = temperature of coolant entering the engine
This formula gives the total heat transferred from the combustion chamber to the cooling liquid.
To proceed with my calculations, I need to know the value of "q", known as "overall heat transfer coefficient" or "average heat transfer rate", between a copper chamber and the coolant (kerosene).
I need this number to find w:
"A", from the first formula, is known: "q" is needed to find the value of Q and finally find the actual cooling liquid flow rate
I'm currently working with Btu, lb, sec, in as units
Thank you in advance