Nozzles with divergence angles of 15, 25 and 29° were tested at area ratios of 10, 25, and 40 at pressure ratios up to 120; sizable thrust gains could be realized by optimizing divergence angle at given surface area ratio; simplified method of thrust determination for conical nozzles permits calculation of thrust in separated flow region from unseparated static-pressure distributions.
Performance of several conical convergent-divergent rocket-type exhaust nozzles
NASA -- Tech Note
1960
31 pages
Report
Englisch
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Acoustic Effect of Chevrons on Supersonic Jets Exiting Conical Convergent-Divergent Nozzles
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