Determination of performance and flow separation characteristics; variables include divergent half-angles from 15 to 30°, area ratios from 8/1 to 75/1, and pressure ratios from 35 to 840; results showed that 20 or 25° half-angles were superior to vacuum conditions; advantage of these over smaller area ratio, 15° half-angle nozzles amounted to about 1% in thrust coefficient.
Experimental study of effects of geometric variables on performance of conical rocket-engine exhaust nozzles
NASA -- Tech Note
1961
61 pages
Report
Englisch
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Performance of several conical convergent-divergent rocket-type exhaust nozzles
Engineering Index Backfile | 1960
|Performance of plug-type rocket exhaust nozzles
Engineering Index Backfile | 1961
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