Five nonfiring propellant pump performance tests of the J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. The tests were accomplished during test period J4-1801-10 at pressure altitudes of approximately 100,000 ft to evaluate the effects of low fuel pump inlet pressure on pump operating characteristics (tests 10A through 10D) and to determine the effects of spinup with dry pumps on test 10E. In the first four tests, liquid nitrogen was utilized as the operating fluid in the oxidizer system for safety reasons and to prevent engine firing on any test. Thrust chamber and turbine components were thermally conditioned before each performance test. (Author)
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