Timeline for In the context of calculating mass flow rate from thrust and Isp, how would an additional efficiency be defined?
Current License: CC BY-SA 4.0
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| Sep 7, 2018 at 11:57 | comment | added | SF. | @uhoh: Thing is raw unburnt fuel in a tank on the launchpad or test stand doesn't have momentum or velocity or such. It has specific energy and mass/volume, which combine into total energy and then all the rest comes from that. It's not momentum or thrust that turns the turbopump. Once you're in the realm of momentum, thrust and velocity, you're already past the point where the losses occurred. | |
| Sep 7, 2018 at 9:24 | comment | added | Hobbes | Many rockets have separate exhaust nozzles for the turbopump, including the Falcon 9. Only staged combustion engines run the turbopump exhaust through the combustion chamber. Some gas generator engines inject the GG exhaust into the nozzle for film cooling. | |
| Sep 7, 2018 at 9:18 | history | answered | SF. | CC BY-SA 4.0 |