Liquid oxygen (LOX) used in a rocket test facility is stored in an insulated tank that is vented to the atmosphere. During a test of the Space Shuttle Main Engine (SSME), the LOX flow rate is required to be 885 lbm/s. The nominal combustion-chamber pressure is 2,970 psia. The LOX storage tank is located 1,000 ft from the engine test stand. Assuming that the liquid oxygen is an incompressible fluid, estimate the pump increase in head and the diameter of the lines required. For this problem use schedule 160 pipe.