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Boundary cooled rocket engines for space storable propellants
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | McFarland, B. L. Gurnitz, R. N. Knight, R. M. Kesselring, R. C. |
| Copyright Year | 1972 |
| Description | An evaluation of an existing analytical heat transfer model was made to develop the technology of boundary film/conduction cooled rocket thrust chambers to the space storable propellant combination oxygen difluoride/diborane. Critical design parameters were identified and their importance determined. Test reduction methods were developed to enable data obtained from short duration hot firings with a thin walled (calorimeter) chamber to be used quantitatively evaluate the heat absorbing capability of the vapor film. The modification of the existing like-doublet injector was based on the results obtained from the calorimeter firings. |
| File Size | 29241136 |
| Page Count | 264 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730004128 |
| Archival Resource Key | ark:/13960/t47q3rg76 |
| Language | English |
| Publisher Date | 1972-06-19 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Diborane Space Storage Liquid Rocket Propellants Cooling Systems Film Cooling Oxygen Fluorides Storable Propellants Heat Transfer 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 |
