At rated thrust, a liquid-fueled rocket motor consumes \(80 \mathrm{~kg} / \mathrm{s}\) of nitric acid as oxidizer and \(32 \mathrm{~kg} / \mathrm{s}\) of aniline as fuel. Flow leaves axially at \(180 \mathrm{~m} / \mathrm{s}\) relative to the nozzle and at \(110 \mathrm{kPa}\) absolute. The nozzle exit diameter is \(D=0.6 \mathrm{~m}\). Calculate the thrust produced by the motor on a test stand at standard sea-level pressure.