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Three dimensional thermal analysis of rocket thrust chambers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Naraghi, M. H. N. Armstrong, E. S. |
| Copyright Year | 1988 |
| Description | A numerical model for the three dimensional thermal analysis of rocket thrust chambers and nozzles has been developed. The input to the model consists of the composition of the fuel/oxidant mixture and flow rates, chamber pressure, coolant entrance temperature and pressure, dimensions of the engine, materials and the number of nodes in different parts of the engine. The model allows for temperature variation in three dimensions: axial, radial and circumferential directions and by implementing an iterative scheme, it provides nodal temperature distribution, rates of heat transfer, hot gas and coolant thermal and transport properties. |
| File Size | 951764 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19890011654 |
| Archival Resource Key | ark:/13960/t1tf4pv7c |
| Language | English |
| Publisher Date | 1988-06-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Nozzle Walls Nozzle Flow Temperature Effects Rocket Engine Cases Thrust Chambers Thermal Analysis 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 |
