ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Sixteen firings of the J-2 rocket engine SN J-2036-1 were conducted. This testing was in support of the J-2 engine application on the S-2 stage of the Saturn 5 vehicle. The firings were conducted utilizing the specially configured low pressure fuel duct designed to simulate the S-2 center engine low pressure fuel duct fluid dynamics. The firings were accomplished at pressure altitudes of approximately 100,000 ft at engine start. The primary objective of these firings was to evaluate the augmented spark igniter. Engine components were thermally conditioned to predicted S-2 interstageengine temperatures. Engine operation was satisfactory on all firings except firing 02D, on which ignition was not detected in the augmented spark igniter. Total accumulated firing duration for the four test periods was 197.0 sec.
Prepared in cooperation with ARO, Inc., Tullahoma, TN.