This paper studies the state of knowledge and the needed improvement in noise methodology and measurements for tilt rotor aircraft. Similarities and differences between tilt rotor aeroacoustic conditions and helicopter and propeller experience are identified. A discussion of the possible principal noise mechanisms throughout the flight envelope shows a need for further experimental and analytical investigations to develop an adequate understanding of the important sources and influencing factors. Existing experimental data from flight tests suggest terminal area noise reduction by operating within certain portions of the conversion flight envelope. Prediction methods are found to provide approximate indications only for low frequency harmonic and broadband noise for several of the tilt rotor's operating conditions. The acoustic effects of the hover case 'fountain' flow are pronounced and need further research. Impulsive noise and high frequency harmonic noise remain problems, as on helicopters, pending major improvements in wake, unsteady aerodynamics, and acoustics methodology.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Tilt rotor aircraft aeroacoustics


    Contributors:

    Publication date :

    1989-05-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Tilt rotor broadband hover aeroacoustics

    Coffen, C.D. / George, A.R. | Tema Archive | 1993


    Aerodynamics and Aeroacoustics of Helicopters and Tilt Rotor Aircraft

    Kloeppel, V. / Commission of the European Communities | British Library Conference Proceedings | 1993


    Four-rotor tilt rotor aircraft

    HONG QUAN / YE HONGCHUAN / CAI TIANXIAO | European Patent Office | 2020

    Free access

    Electric tilt rotor aircraft

    FENG XUBI / HE HAIBIN / YANG CHAO et al. | European Patent Office | 2022

    Free access

    TILT-ROTOR AIRCRAFT WING

    KIM CHEOL WAN / LEE YUNG GYO | European Patent Office | 2016

    Free access