Timeline for How to calculate the thrust of a rocket with relativistic exhaust
Current License: CC BY-SA 3.0
7 events
| when toggle format | what | by | license | comment | |
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| Apr 16, 2017 at 13:15 | comment | added | pr1268 | Just as an aside: the $I_{sp}$ of that rocket motor would be around 29.4 million seconds (almost a whole year)! | |
| Jan 2, 2016 at 15:02 | comment | added | Kyle Kanos | Technically, the general thrust equation is $F=\dot{m}_ev_e+(p_e-p_0)A_e$ where $p_i$ are the exhaust & ambient pressures and $A_e$ the cross-sectional area of the nozzle. You've cited for the (ideal) case of $p_e=p_0$. | |
| S Jan 2, 2016 at 12:35 | history | suggested | Wang Yun | CC BY-SA 3.0 |
Improved formatting
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| Jan 2, 2016 at 10:59 | review | Suggested edits | |||
| S Jan 2, 2016 at 12:35 | |||||
| Dec 25, 2015 at 18:52 | vote | accept | S. Hale | ||
| Dec 25, 2015 at 11:04 | answer | added | John Rennie | timeline score: 3 | |
| Dec 25, 2015 at 1:39 | history | asked | S. Hale | CC BY-SA 3.0 |