"An Apollo Service Module contour engine [Aerojet AJ10-137] mounted in the Propulsion Systems Laboratory at NASA Lewis Research Center in 1964. The Laboratory contained two 14-foot diameter test chambers that could simulate conditions found at very high altitudes. Researchers sought to determine the impulse value of the storable propellant mix, classify and improve the internal engine performance, and compare the results with analytical tools. A special setup was installed in the chamber that included a device to measure the thrust load and a calibration stand."
This engine used Aerozine 50 (a 1:1 mix of UDMH and hydrazine) as fuel and nitrogen tetroxide (N2O4) as an oxidizer, rather than the previous nitric acid/UDMH.
Three different noozles for testing: a 15 degree conical nozzle, a Titan transtage contour nozzle and an Apollo AJ10-137.
Date: 1964
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NASA ID: C-1964-68789, C-1964-70930, C-1964-70929, C-1964-70931, C-1964-69633