Timeline for How fast could a fully fueled Falcon 9 go to propellant depletion if started in a vacuum
Current License: CC BY-SA 4.0
8 events
| when toggle format | what | by | license | comment | |
|---|---|---|---|---|---|
| Jan 29, 2020 at 13:48 | vote | accept | Stickyz | ||
| Jan 29, 2020 at 1:49 | answer | added | Russell Borogove | timeline score: 1 | |
| Jan 28, 2020 at 4:24 | answer | added | uhoh | timeline score: 0 | |
| Jan 27, 2020 at 23:24 | comment | added | Avi Cherry | Here's a figure of 1.3-1.8km/s total drag to LEO, with a reference | |
| Jan 27, 2020 at 23:17 | comment | added | Avi Cherry | The fact that the rocket is launching in a vacuum would be insignificant compared to the fact that the rocket would already be in orbit, meaning it would already be travelling at 8km/s. A launch with a reasonable ascent profile does not actually waste very much energy overcoming the atmosphere. | |
| Jan 27, 2020 at 23:02 | comment | added | Christopher James Huff | Several issues: first, due to the Oberth effect, it matters a great deal when, where, and in what direction you perform your burn. Second, just computing the delta-v available relies on details of the Falcon 9's mass ratios and stage dry masses that can only be estimated from public information; as Russell Borogove mentioned, the engines don't fit; and the Falcon 9 upper stage can only last a few hours due to LOX boiling off, RP-1 getting cold and gelling, and batteries running down. You're better off fully defining a Falcon 9-like vehicle. | |
| Jan 27, 2020 at 22:07 | comment | added | Russell Borogove | The vacuum optimization for Merlin involves adding a very large engine nozzle extension; there wouldn't be room for 9 of them at the base of the first stage. | |
| Jan 27, 2020 at 21:27 | history | asked | Stickyz | CC BY-SA 4.0 |