Propulsion airframe aeroacoustic integration effects for a hybrid wing body aircraft configuration

International Journal of Aeroacoustics

Volumn 11, Issue 3-4, 2012, Pages 335-368

  Czech, Michael ^a   Thomas, Russell ^b   Elkoby, Ronen ^a  

^a BOEING COMPANY   (United States)

^b NASA LANGLEY RESEARCH CENTER   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AIRFRAME MODEL; AXISYMMETRIC; CHEVRON NOZZLE; DIRECTIVITY ANGLE; EXPERIMENTAL INVESTIGATIONS; FORWARD FLIGHT; GAS CONDITIONS; HIGH BYPASS RATIO ENGINES; HIGH FREQUENCY; JET NOISE; JET NOZZLE; LOW FREQUENCY; LOW-FREQUENCY NOISE; MID-FREQUENCY; NOISE SOURCE; NOZZLE CONFIGURATION; NOZZLE EXITS; PLANFORM; POLAR ANGLES; SHIELDING EFFECTIVENESS; SPECTRAL CHANGE; TRAILING EDGES; UPSTREAM MIGRATION; WING BODY AIRCRAFT; WING TRAILING EDGE;

ACOUSTIC NOISE MEASUREMENT; AEROACOUSTICS; AIRFRAMES; BYPASS RATIO; MAGNETIC SHIELDING; NOISE ABATEMENT; NOZZLES; PLANFORMS; PROPULSION; STRUCTURAL FRAMES; TRANSPORT AIRCRAFT;

ACOUSTIC NOISE;

EID: 84864602679     PISSN: 1475472X     EISSN: None     Source Type: Journal    
DOI: 10.1260/1475-472X.11.3-4.335     Document Type: Article

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