Reduction of helicopter blade-vortex interaction noise by active rotor control technology

Progress in Aerospace Sciences

Volumn 33, Issue 9-10, 1997, Pages 647-687

  Yu, Yung H ^a   Gmelin, Bernd ^b   Splettstoesser, Wolf ^b   Philippe, Jean J ^c   Prieur, Jean ^c   Brooks, Thomas F ^d  

^a NASA AMES RESEARCH CENTER   (United States)

^b GERMAN AEROSPACE CENTER DLR   (Germany)

^c ONERA   (France)

^d NASA LANGLEY RESEARCH CENTER   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; CONTROL SYSTEMS; HELICOPTER ROTORS; TECHNOLOGY; TURBOMACHINE BLADES; VORTEX FLOW;

HARMONIC PITCH CONTROL; HELICOPTER BLADE VORTEX INTERACTION NOISE; INDIVIDUAL BLADE CONTROL; ON BLADE CONTROL; ROTOR CONTROL TECHNOLOGY;

ACOUSTIC VARIABLES CONTROL;

EID: 0031223475     PISSN: 03760421     EISSN: None     Source Type: Journal    
DOI: 10.1016/S0376-0421(97)00006-7     Document Type: Review

References (50)

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