Experimental data obtained in this study (Part II) complement the speciation data presented in Part I, but also offer a basis for extensive facility cross-comparisons for both experimental ignition delay time (IDT) and laminar flame speed (LFS) observables.To improve understanding of the ignition characteristics of propene, a series IDT experiments were performed in six different shock tubes and two rapid compression machines (RCMs) under conditions not previously studied. This study is the first of its kind to directly compare ignition in several different shock tubes over a wide range of conditions. For common nominal reaction conditions among these facilities, cross-comparison of shock tube IDTs suggests 20-30% reproducibility (2σ) for the IDT observable. The combination of shock tube and RCM data greatly expands the data available for validation of propene oxidation models to higher pressures (2-40 atm) and lower temperatures (750-1750 K).Propene flames were studied at pressures from 1-20 atm and unburned gas temperatures of 295-398 K for a range of equivalence ratios and dilutions in different facilities. The present propene-air LFS results at 1 atm were also compared to LFS measurements from the literature. With respect to initial reaction conditions, the present experimental LFS cross-comparison is not as comprehensive as the IDT comparison; however, it still suggests reproducibility limits for the LFS observable. For the LFS results, there was agreement between certain data sets and for certain equivalence ratios (mostly in the lean region), but the remaining discrepancies highlight the need to reduce uncertainties in laminar flame speed experiments amongst different groups and different methods. Moreover, this is the first study to investigate the burning rate characteristics of propene at elevated pressures (> 5 atm).IDT and LFS measurements are compared to predictions of the chemical kinetic mechanism presented in Part I and good agreement is observed.

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All satellites must be disposed of at end-of-life per the policy of the United States Strategic Command; therefore, enough propellant must be reserved to reach the intended graveyard orbit. The accuracy of fuel estimation techniques directly ties to the available propellant for on-orbit use and extended life. The Aerospace Corporation has developed an estimation algorithm for the Defense Satellite Communication System III to accurately predict fuel remaining based on pressure and temperature telemetry, thruster characteristics, and burn durations. These results are validated with flight data. NomenclatureDSCS III = Defense Satellite Communication System III Z = Compressibility factor g = Gravitational constant ΔV = Change of velocity Isp = Specific impulse Δw = Fuel used since isolation lbf = Pound force ρ = Density M = Vehicle mass σ = Standard Deviation N = Newton n = Number of moles Subscripts P = Pressure 1 = Tank 1 PVT = Pressure, Volume, Temperature 3 = Tank 3 R = Universal gas constant A = Bank A RDV = Revised Delta-V dep = Depletion T = Temperature g = Gas V = Volume i = Initial w = Fuel mass iso = Isolation X = Dependent parameter res = Residual

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