Flow in overexpanded supersonic nozzles reviewed; although 5 flow regimes can be discerned, depending on nozzle pressure ratio, regime of most interest is one characterized by oblique shock patterns in nozzle and flow separation from nozzle wall; pressure rise associated with separation correlates well with Mach number at separation point; formulation for pressure rise required to separate flow provides excellent agreement with experimental data over wide range of operating conditions and prediction of nozzle performance.
Shock-induced boundary layer separation in overexpanded conical exhaust nozzles
AIAA J
AIAA Journal ; 1 , n 3
1963
4 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Modeling Free Shock Separation Induced Side Loads in Overexpanded Rocket Nozzles
Online Contents | 2015
|Separation Instabilities in Overexpanded Nozzles
AIAA | 2003
|SEPARATION INSTABILITIES IN OVEREXPANDED NOZZLES
British Library Conference Proceedings | 2003
|FLOW SEPARATION IN OVEREXPANDED CONTOURED NOZZLES
AIAA | 1963
|