Chapter 1, Problem 1.51P

The inner wall of a rocket motor combustion chamber receives ${\text{160 kW/m}}^{\text{2}}$ by radiation from a gas at $\text{2760°C}$. The convection heat transfer coefficient between the gas and the wall is $\text{110W/}\left({\text{m}}^{\text{2}}\text{K}\right)$. If the inner wall of the combustion chamber is at

Problem 1.51

a temperature of $\text{540°C}$, determine (a) the total thermal resistance of a unit area of the wall in $\left({\text{m}}^{\text{2}}\text{K}\text{.}\right)\text{/W}$ and (b) the heat flux. Also draw the thermal circuit.