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Theoretical performance of hydrogen-oxygen rocket thrust chambers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1961 |
| Description | Data are presented for liquid-hydrogen-liquid-oxygen thrust chambers at chamber pressures from 15 to 1200 pounds per square inch absolute, area ratios to approximately 300, and percent fuel from about 8 to 34 for both equilibrium and frozen composition during expansion. Specific impulse in vacuum, specific impulse, combustion-chamber temperature, nozzle-exit temperature, characteristic velocity, and the ratio of chamber-to-nozzle-exit pressure are included. The data are presented in convenient graphical forms to allow quick calculation of theoretical nozzle performance with over- or underexpansion, flow separation, and introduction of the propellants at various initial conditions or heat loss from the combustion chamber. |
| File Size | 14561587 |
| Page Count | 82 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980227353 |
| Archival Resource Key | ark:/13960/t4mm1285w |
| Language | English |
| Publisher Date | 1961-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power 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 |
