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Size: 770
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← Revision 9 as of 2019-06-17 02:16:22 ⇥
Size: 788
Comment:
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| Deletions are marked like this. | Additions are marked like this. |
| Line 12: | Line 12: |
| ||<-3>|| ||<-3>|| || Laser Ablation Thrust || 2.95 || 2.50 || |
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| Line 13: | Line 16: |
| || Laser Ablation Thrust || 2.95 || 2.50 || |
Rocket Engines
Contemplating the expansion ratio and mach number of miscellaneous high-expansion rocket engines. The mach number is from Figure 3.1 on page 39 of Sutton, assuming a specific heat ratio of 1.3:
|
ratio |
mach |
Saturn V first stage F1 |
16.1 |
4.01 |
Saturn V 2nd/3rd J2 |
27.5 |
4.50 |
Apollo SM AJ10-137 |
62.5 |
5.31 |
Shuttle SSME RS-25 |
77.5 |
5.53 |
SpaceX Merlin Vacuum 1C |
14.5 |
3.91 |
SpaceX Merlin Vacuum 1D |
165 |
6.36 |
Laser Ablation Thrust |
2.95 |
2.50 |
from Phipps and Michaelis 1994; can we do better? |
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note = Atlas sustainer was central engine used after the two outer booster engines were jettisoned.