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A two-dimensional finite difference program for thermal analysis of rocket thrust chambers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Naraghi, Mohammad H. |
| Copyright Year | 1987 |
| Description | A two-dimensional finite difference computer model for thermal analysis of rocket thrust chambers has been developed. The model uses an iterative scheme for calculating the temperature distribution within the chamber wall and implements a successive overrelaxation formula for a quick convergence. The inputs of the models are the dimensions of the thrust chamber wall, types of materials used, heat transfer coefficients and temperatures of the hot gas and the coolant. The resulting output of the program consists of the nodal temperature distribution, heat transfer to the coolant and heat transfer from the hot gas. |
| File Size | 1406673 |
| Page Count | 53 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880003157 |
| Archival Resource Key | ark:/13960/t4rj9bj5c |
| Language | English |
| Publisher Date | 1987-09-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Temperature Distribution Finite Difference Theory Rocket Thrust Dimensions Coolants Rocket Engines Thrust Chambers Computerized Simulation High Temperature Gases Thermal Analysis Heat Transfer Coefficients 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 |
