Figure 34: Recovered Combustion Chamber Pieces Figure 37: Rocket Wake Figure 38: Rocket Nose Cone Boundary Layer 6.3 Tables and Plots Parameter Units Isp Specific Impulse, ideal sec. 164 Isp Specific Impulse, measured 137 sec. C* Characteristic exhaust velocity, ft/s (m/s) 2993 (912) theoretical C* Characteristic exhaust velocity, 2922 (891) ft/s (m/s) measured To Combustion temperature, theoretical deg Celsius (K) 1437 (1710) @1000 psia Density, ideal 1.879 gram/cu.cm. Density, as cast 1.859 gram/cu.cm. X Mass fraction of condensed-phase - 0.425 products k Ratio of specific heats - 1.043 M Effective molecular wt. of exhaust g/mole 42.39 products Burn rate behavior plateau ro Burn rate @ 1 atm. in/sec 0.084 r Burn rate @ 1000 psia in/sec 0.509 Tcr Auto-ignition temperature deg. C. > 300
Figure 34: Recovered Combustion Chamber Pieces Figure 37: Rocket Wake Figure 38: Rocket Nose Cone Boundary Layer 6.3 Tables and Plots Parameter Units Isp Specific Impulse, ideal 164 sec. Isp Specific Impulse, measured 137 sec. C* Characteristic exhaust velocity, theoretical 2993 (912) ft/s (m/s) C* Characteristic exhaust velocity, measured 2922 (891) ft/s (m/s) To Combustion temperature, theoretical @1000 psia 1437 (1710) deg Celsius (K) Density, ideal 1.879 gram/cu.cm. Density, as cast 1.859 gram/cu.cm. X Mass fraction of condensed-phase products 0.425 - k Ratio of specific heats 1.043 - M Effective molecular wt. of exhaust products 42.39 g/mole Burn rate behavior plateau ro Burn rate @ 1 atm. 0.084 in/sec r Burn rate @ 1000 psia 0.509 in/sec Tcr Auto-ignition temperature > 300 deg. C.