1. Configuration
2. Chamber Pressure (psia) Mixture Ratio (O/F) Throat Diameter(inch) Chamber Diameter (inch) Contraction Ratio Oxidizer Flowrate (Ibm/sec) Fuel Flowrate (Ibm/sec) Total Flowrate (Ibm/sec) Theoretical C* (ft/sec) 25K Configuration
3. 250 2.4 9.56 18.2 3.6 74.1 30.9 105 5827 40K Configuration
4. through the nozzle. !n this manner, a pintle tip could be changed in a matter of minutes. The fuel rings, also replaceable, required removal of the engine from the test stand, and removal of the injector fromthe chamber to change. The baseline pintie tip geometry for the 25K thrust configuration was scaled directly from the 13K LOX/RP-1 engine tested at NASA LeRC in 1995. This engine achieved 95% C* efficiency, thuswas a good starting point for design purposes. Three other tips were made for the 25K configuration, exploring slot geometry effects on performance including blockage ratio (slot width to land ratio), percent flow in the secondary slots, and total slot number.