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A performance comparison of two small rocket nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Arrington, Lynn A. Reed, Brian D. Rivera Jr., Angel |
| Copyright Year | 1996 |
| Description | An experimental study was conducted on two small rockets (110 N thrust class) to directly compare a standard conical nozzle with a bell nozzle optimized for maximum thrust using the Rao method. In large rockets, with throat Reynolds numbers of greater than 1 x 10(exp 5), bell nozzles outperform conical nozzles. In rockets with throat Reynolds numbers below 1 x 10(exp 5), however, test results have been ambiguous. An experimental program was conducted to test two small nozzles at two different fuel film cooling percentages and three different chamber pressures. Test results showed that for the throat Reynolds number range from 2 x 10(exp 4) to 4 x 10(exp 4), the bell nozzle outperformed the conical nozzle. Thrust coefficients for the bell nozzle were approximately 4 to 12 percent higher than those obtained with the conical nozzle. As expected, testing showed that lowering the fuel film cooling increased performance for both nozzle types. |
| File Size | 672091 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960050633 |
| Archival Resource Key | ark:/13960/t19k98j4j |
| Language | English |
| Publisher Date | 1996-08-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Rocket Nozzles Conical Nozzles Nozzle Design Performance Tests Reynolds Number Thrust Chamber Pressure Rocket Thrust Nozzle Thrust Coefficients Low Thrust Specific Impulse Film Cooling Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
