Propellant Table
| To approximate Isp at other chamber pressures | |
|---|---|
| Absolute Pressure (atm) {psi} | Multiply by |
| 6,895 kPa (68.05) {1000} | 1.00 |
| 6,205 kPa (61.24) {900} | 0.99 |
| 5,516 kPa (54.44) {800} | 0.98 |
| 4,826 kPa (47.63) {700} | 0.97 |
| 4,137 kPa (40.83) {600} | 0.95 |
| 3,447 kPa (34.02) {500} | 0.93 |
| 2,758 kPa (27.22) {400} | 0.91 |
| 2,068 kPa (20.41) {300} | 0.88 |
JANAF thermochemical data used throughout. Calculations performed by Rocketdyne, results appear in "Modern Engineering for Design of Liquid-Propellant Rocket Engines", Huzel and Huang. Some of the units have been converted to metric, but pressures have not. These are best-possible specific impulse calculations.
Assumptions:
- adiabatic combustion
- isentropic expansion
- one-dimensional expansion
- shifting equilibrium
Read more about this topic: Liquid Rocket Propellants
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