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Temperature histories in ceramic-insulated heat-sink nozzle
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1960 |
| Description | Temperature histories were calculated for a composite nozzle wall by a simplified numerical integration calculation procedure. These calculations indicated that there is a unique ratio of insulation and metal heat-sink thickness that will minimize total wall thickness for a given operating condition and required running time. The optimum insulation and metal thickness will vary throughout the nozzle as a result of the variation in heat-transfer rate. The use of low chamber pressure results in a significant increase in the maximum running time of a given weight nozzle. Experimentally measured wall temperatures were lower than those calculated. This was due in part to the assumption of one-dimensional or slab heat flow in the calculation procedure. |
| File Size | 1040584 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980227786 |
| Archival Resource Key | ark:/13960/t86h9918g |
| Language | English |
| Publisher Date | 1960-07-01 |
| Access Restriction | Open |
| Subject Keyword | Nonmetallic Materials 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 |
