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A study of injection processes for 15-percent fluorine - 85-percent oxygen and heptane in a 200-pound-thrust rocket engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1957 |
| Description | Characteristic exhaust velocity over a range of mixture ratios and variations in gas velocity with distance from the injector were measured for six injectors. Comparisons of injector performance showed the gains obtained from oxidant atomization, fuel atomization, and propellant mixing. The results are compared with oxygen and heptane performance and show the effect, which is qualitatively small, of spontaneous propellant ignition on the relation between injection processes and engine performance. |
| File Size | 1243310 |
| Page Count | 25 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930089480 |
| Archival Resource Key | ark:/13960/t2f81322m |
| Language | English |
| Publisher Date | 1957-01-15 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
