Unsteadiness of flow separation and end-effects regime in a thrust-optimized contour rocket nozzle

DOI10.1023/B:APPL.0000014927.61427.ADzbMath1113.76301OpenAlexW2091931338MaRDI QIDQ1430081

D. Massart

Publication date: 27 May 2004

Published in: Flow, Turbulence and Combustion (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1023/b:appl.0000014927.61427.ad

zbMATH Keywords

nozzleside loadsfree shock separationrestricted shock separation

Mathematics Subject Classification ID

Experimental work for problems pertaining to fluid mechanics (76-05)

Related Items (7)

Nozzle flow separation ⋮ Delayed detached eddy simulation of the end-effect regime and side-loads in an overexpanded nozzle flow ⋮ Transient three-dimensional startup side load analysis of a regeneratively cooled nozzle ⋮ Shock wave boundary layer interaction ⋮ Flow dynamics and wall-pressure signatures in a high-Reynolds-number overexpanded nozzle with free shock separation ⋮ Unsteadiness in shock-induced separated flow with subsequent reattachment of supersonic annular jet ⋮ Jet resonance in truncated ideally contoured nozzles

This page was built for publication: Unsteadiness of flow separation and end-effects regime in a thrust-optimized contour rocket nozzle