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Rocket engine thrust chamber wall temperature distribution calculation and analysis
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Saha, H. |
| Copyright Year | 1976 |
| Description | An analytical computational concept is presented which predicts the temperature profiles along a regeneratively cooled thrust chamber wall on the hot gas side and on the coolant side, and also the coolant bulk temperature profile. The computational model is based upon a coupling of the boundary layer heat transfer process with the heat transfer process through the chamber wall and the coolant flow heat absorption. The calculation is started with approximate temperature distributions for the hot gas side wall and the coolant flow. The iteration process of the computer program is terminated when the total heat transfer rates from the hot gas boundary layer to the wall and from the wall to the coolant are equal. The computer program for the integration of regenerative cooling process to a thrust chamber is kept general such that this program can be used with any boundary layer analysis computer program for temperature profile and heat transfer studies. A sample application of this concept is shown by using a boundary layer analysis program for the RL10 rocket engine thrust chamber. |
| File Size | 1954700 |
| Page Count | 41 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760019183 |
| Archival Resource Key | ark:/13960/t0vq7qk17 |
| Language | English |
| Publisher Date | 1976-05-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Wall Temperature Rocket Engine Cases Thrust Chambers Computerized Simulation Temperature Profiles Prediction Analysis Techniques Radiative Heat Transfer Regenerative Cooling 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 |
