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Computer code for single-point thermodynamic analysis of hydrogen/oxygen expander-cycle rocket engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Glassman, Arthur J. Jones, Scott M. |
| Copyright Year | 1991 |
| Description | This analysis and this computer code apply to full, split, and dual expander cycles. Heat regeneration from the turbine exhaust to the pump exhaust is allowed. The combustion process is modeled as one of chemical equilibrium in an infinite-area or a finite-area combustor. Gas composition in the nozzle may be either equilibrium or frozen during expansion. This report, which serves as a users guide for the computer code, describes the system, the analysis methodology, and the program input and output. Sample calculations are included to show effects of key variables such as nozzle area ratio and oxidizer-to-fuel mass ratio. |
| File Size | 1242825 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910010893 |
| Archival Resource Key | ark:/13960/t7dr7rq82 |
| Language | English |
| Publisher Date | 1991-04-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Gas Composition Thermodynamics Chemical Equilibrium Reaction Kinetics Systems Analysis Hydrogen Oxygen Engines Mass Ratios Combustion Chambers Propellant Combustion Turbines User Manuals Computer Programs Computer Programs 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 |
