| Propellant Heats of Formation, Hydrogen Atoms, Oxygen Atoms & Densities | ||||
| Propellant | Heat of Formation ( J / kmol ) | Hydrogen | Oxygen | Density ( kg / m^3 ) |
| Water | -285,830,000 |
2 |
1 |
997.000 |
| Water at 373 K | -280,183,000 |
2 |
1 |
958.400 |
| Water at 394 K | -278,600,000 |
2 |
1 |
944.000 |
| Water at 452 K | -274,240,000 |
2 |
1 |
903.000 |
| Water at 531 K | -268,310,000 |
2 |
1 |
848.000 |
| Water at 624 K | -261,290,000 |
2 |
1 |
784.000 |
| Steam at 373 K | -239,300,000 |
2 |
1 |
0.588 |
| Steam at 394 K | -238,595,000 |
2 |
1 |
0.557 |
| Steam at 452 K | -236,647,000 |
2 |
1 |
0.485 |
| Steam at 531 K | -233,995,000 |
2 |
1 |
0.413 |
| Steam at 624 K | -230,872,000 |
2 |
1 |
0.351 |
| Hydrogen | -8,123,000 |
2 |
0 |
70.800 |
Propellant oxygen is the number of oxygen atoms in a propellant molecule. Oxygen has six electrons in an outer shell which can comfortably hold eight and therefore tends to pull two electrons from neighbouring atoms. Propellants that are high in oxygen generally have a higher density than propellants that are low in oxygen.
Propellants high in oxygen are used when high thrust is important, for instance, water injected rockets operating at low altitude. Propellants low in oxygen are used when high exhaust velocity is important, for instance, electrically heated low thrust rockets for use in space Propellant oxygen is used to calculate propellant molecular and propellant oxidation.
propellant molecular = propellant hydrogen + 16 * propellant oxygen
propellant oxidation = 2 * propellant oxygen - propellant hydrogen
This is used in tripropellant rocket, pumped rocket and rocket cost.
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