(Solved): Hint: (the heat transfer on the rocket engine): you can assume the walls as planar. The assumption ...

Hint: (the heat transfer on the rocket engine): you can assume the walls as planar. The assumption works because the chamber is very large and the walls are very thin by comparison. Therefore, there is no significant change radially across the wall. This way you can use the thermal resistors relations from the planar wall.

A liquid propellant rocket combustor is regeneratively cooled and is characterized by: - Chamber temperature: \( \mathrm{Tg}=2750 \mathrm{~K} \) - Coolant bulk temperature: \( T \mathrm{c}=300 \mathrm{~K} \) - Wall thickness: \( t w=2 \mathrm{~mm} \) - The following heat coefficients: \( \mathrm{kw}=43 \mathrm{~W} / \mathrm{m}-\mathrm{K} ; \mathrm{hg}=657 \mathrm{~W} / \mathrm{m} 2-\mathrm{K} ; \mathrm{hc}=26,000 \mathrm{~W} / \mathrm{m} 2-\mathrm{K} \) Calculate: (a) The total heat flux (b) The wall temperature on the gas side \( T_{w g} \) (c) The wall temperature on the coolant side \( \mathrm{T}_{\mathrm{wc}} \)