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Numerical simulation of film-cooled ablative rocket nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Beard, R. M. Landrum, D. B. |
| Copyright Year | 1996 |
| Description | The objective of this research effort was to evaluate the impact of incorporating an additional cooling port downstream between the injector and nozzle throat in the NASA Fast Track chamber. A numerical model of the chamber was developed for the analysis. The analysis did not model ablation but instead correlated the initial ablation rate with the initial nozzle wall temperature distribution. The results of this study provide guidance in the development of a potentially lighter, second generation ablative rocket nozzle which maintains desired performance levels. |
| File Size | 1133820 |
| Page Count | 39 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960028559 |
| Archival Resource Key | ark:/13960/t3kx0bc84 |
| Language | English |
| Publisher Date | 1996-04-26 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Rocket Nozzles Nozzle Geometry Temperature Distribution Throats Nozzle Walls Injectors Gas Cooling Computational Fluid Dynamics Coolants Ablative Materials Computerized Simulation Copper 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 |
