Timeline for Is it possible to estimate the nozzle characteristics of the Rocketdyne HG3 engine?
Current License: CC BY-SA 3.0
9 events
| when toggle format | what | by | license | comment | |
|---|---|---|---|---|---|
| Jan 8, 2017 at 4:06 | vote | accept | Alastair Haslam | ||
| Jan 7, 2017 at 23:32 | history | tweeted | twitter.com/StackSpaceExp/status/817876657956655104 | ||
| S Jan 7, 2017 at 20:13 | history | suggested | Martin Schröder | CC BY-SA 3.0 |
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| Jan 7, 2017 at 12:46 | review | Suggested edits | |||
| S Jan 7, 2017 at 20:13 | |||||
| Jan 6, 2017 at 22:00 | answer | added | TRF | timeline score: 6 | |
| Jan 6, 2017 at 14:57 | comment | added | Organic Marble | I had not heard of the HG-3 until this post, I will have to read up on it. | |
| Jan 6, 2017 at 14:56 | comment | added | Alastair Haslam | @OrganicMarble Ah yes, thought that figure was familiar. Do you think that the HG-3 may have sported the original combustion chamber dimensions of the SSME? I've read that it was developed from the HG-3, but I'm not sure how close that relationship was. Perhaps the larger RS-25 chamber was to assist in achieving thrust levels above 500,000 pounds, well beyond the power of its forerunner. | |
| Jan 6, 2017 at 14:01 | comment | added | Organic Marble | The original SSME design area ratio was 77.5. It dropped when they went to the Large Throat Main Combustion Chamber (first flight 2001). | |
| Jan 6, 2017 at 12:10 | history | asked | Alastair Haslam | CC BY-SA 3.0 |