| Display title | Engineering:Regenerative cooling (rocketry) |
| Default sort key | Regenerative cooling (rocketry) |
| Page length (in bytes) | 12,435 |
| Namespace ID | 3034 |
| Namespace | Engineering |
| Page ID | 535901 |
| Page content language | en - English |
| Page content model | wikitext |
| Indexing by robots | Allowed |
| Number of redirects to this page | 0 |
| Counted as a content page | Yes |
| HandWiki item ID | None |
| Edit | Allow all users (infinite) |
| Move | Allow all users (infinite) |
| Page creator | imported>S.Timg |
| Date of page creation | 23:42, 3 February 2024 |
| Latest editor | imported>S.Timg |
| Date of latest edit | 23:42, 3 February 2024 |
| Total number of edits | 1 |
| Recent number of edits (within past 90 days) | 0 |
| Recent number of distinct authors | 0 |
Description | Content |
Article description: (description)
This attribute controls the content of the description and og:description elements. | Regenerative cooling, in the context of rocket engine design, is a configuration in which some or all of the propellant is passed through tubes, channels, or in a jacket around the combustion chamber or nozzle to cool the engine. This is effective because the propellants are often cryogenic. The heated... |
