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Combustion effects on film cooling
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rousar, D. C. Ewen, R. L. |
| Copyright Year | 1977 |
| Description | The effects of: (1) a reactive environment on film cooling effectiveness, and (2) film cooling on rocket engine performance were determined experimentally in a rocket thrust chamber assembly operating with hydrogen and oxygen propellants at 300 psi chamber pressure. Tests were conducted using hydrogen, helium, and nitrogen film coolants in an instrumented, thin walled, steel thrust chamber. The film cooling, performance loss, and heat transfer coefficient data were correlated with the ALRC entrainment film cooling model which relates film coolant effectiveness and mixture ratio at the wall to the amount of mainstream gases entrained with the film coolant in a mixing layer. In addition, a comprehensive thermal analysis computer program, HOCOOL, was prepared from previously existing ALRC computer programs and analytical techniques. |
| File Size | 5514034 |
| Page Count | 196 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770014416 |
| Archival Resource Key | ark:/13960/t0zp8tj3z |
| Language | English |
| Publisher Date | 1977-02-24 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Helium Film Liquid Cooling Rocket Engines Thrust Chambers Film Cooling Combustion Chambers Combustion Efficiency 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 |
