Vortex shedding in a large solid rocket motor without inhibitors at the segment interfaces

Journal of Propulsion and Power

Volumn 13, Issue 2, 1997, Pages 197-206

  Dotson, K W ^a,b,c   Koshigoe, S ^a,c,d   Pace, K K ^a,c,e  

^a AEROSPACE CORPORATION   (United States)

^b Structural Dynamics Department   (United States)

^c AIAA   (United States)

^d Fluid Mechanics Department   (United States)

^e Propulsion Department   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

ACOUSTICS; AERODYNAMIC LOADS; COMBUSTION; NOZZLES; NUMERICAL ANALYSIS; OSCILLATIONS; PRESSURE EFFECTS; ROCKET ENGINES; VORTEX FLOW; VORTEX SHEDDING;

ACOUSTIC FEEDBACK; INTERNAL ACOUSTIC RESPONSE; PRESSURE OSCILLATION; SEGMENT INTERFACES; SOLID ROCKET MOTORS; STATIC FIRING TESTS;

AERODYNAMICS;

EID: 0031096511     PISSN: 07484658     EISSN: 15333876     Source Type: Journal    
DOI: 10.2514/2.5170     Document Type: Article

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