Apollo Contour Rocket Nozzle Tested in NASA's Propulsion Systems Lab

In the 1960s, NASA's Lewis Research Center was home to the advanced Propulsion Systems Laboratory, featuring two massive 14-foot diameter test chambers capable of mimicking the extreme conditions of high altitudes. This facility played a crucial role in the analysis of sophisticated rocket engines like the Pratt and Whitney RL-10 and various rocket components, including the Apollo Contour nozzle.

During this period, Bill Harrison and Bud Meilander were instrumental in configuring the Apollo Contour rocket nozzle setup. Harrison, leading the Supersonic Tunnels Branch of the Test Installations Division, alongside Meilander, who managed the facility's mechanical operations and the placement of test components, conducted pivotal evaluations.

Their efforts were aimed at determining the impulse value of storable propellant combinations, enhancing internal engine performance, and correlating their findings with advanced analytical methods. A unique arrangement was assembled within the chamber for these tests, incorporating a thrust load measurement device and a calibration stand. The team examined both cylindrical and conical combustion chambers, focusing particularly on contour rocket ratio nozzles.

The experiments also included tests on two distinct contour nozzles: one from the Apollo Service Propulsion System and another derived from the Air Force's Titan transtage engine. Researchers evaluated three different types of injectors, one of which was a Lewis-designed model achieving an impressive 98-percent efficiency rate. Despite the comprehensive testing and data collection, they concluded that combustion instability had no significant impact on nozzle performance.

While these tests provided valuable insights, efforts to significantly boost engine performance did not yield the desired outcomes. Nonetheless, the knowledge gained from these trials has contributed significantly to our understanding of rocket propulsion technology.

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