Question: A large rocket engine designed to propel a satellite launcher has a thrust of 106 lbf when operating at sea level, the exit plane pressure being equal to the ambient pressure under these conditions. The combustion chamber pressure and temperature are 500 psia and 4500°F, respectively. If the products of combustion can be assumed to have the properties of air and if the flow through the nozzle can be assumed to be isentropic, find the throat and exit diameters of the nozzle.