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Theoretical rocket performance of liquid methane with several fluorine-oxygen mixtures assuming frozen composition
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1958 |
| Description | Theoretical rocket performance for frozen composition during expansion was calculated for liquid methane with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. The maximum calculated value of specific impulse for a chamber pressure of 600 pounds per square inch absolute (40.827atm) and an exit pressure of 1 atmosphere is 315.3 for 79.67 percent fluorine in the oxidant. |
| File Size | 2127059 |
| Page Count | 45 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930089999 |
| Archival Resource Key | ark:/13960/t8pc7qh8x |
| Language | English |
| Publisher Date | 1958-05-20 |
| 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 |
