At rated thrust, a liquid-fueled rocket motor consumes 180 lbm/s of nitric acid as oxidizer and 70 lbm/s of aniline as fuel. Flow leaves axially at 6000 ft/s relative to the nozzle and at 16.5 psia. The nozzle exit diameter is D = 2 ft. Calculate the thrust produced by the motor on a test standard sea-level pressure draw the rocket horizontally such that the direction of motion is to the right. Let the positive x-axis point to the left).