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.