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Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Pavli, Albert J. Jankovsky, Robert S. Kazaroff, John M. |
| Copyright Year | 1996 |
| Description | An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse. |
| File Size | 12845060 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960042495 |
| Archival Resource Key | ark:/13960/t8md3vp24 |
| Language | English |
| Publisher Date | 1996-06-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Rocket Nozzles Atmospheric Pressure Turbulent Boundary Layer Nozzle Thrust Coefficients Altitude Tests Nozzle Efficiency Wall Temperature Nozzle Geometry Exhaust Velocity Nozzle Walls Thrust Chamber Pressure Liquid Oxygen Divergent Nozzles Specific Impulse Liquid Hydrogen Mass Flow 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 |
