In a major cooperative program between U.S. Government agencies (represented by the U.S. Army Aeroflightdynamics Directorate and NASA Ames and Langley Research Centers) and United Technologies Corp. A 1/6 geometrically and aeroelastically scaled UTC model helicopter rotor was tested in the open-jet anechoic test section of the Duits-Nederlandse Windtunnel in the Netherlands. As the fourth entry under the Aerodynamic and Acoustic Testing of Model Rotors Program, several comprehensive acoustic and aerodynamic databases were obtained relating the important aerodynamic phenomena to both the near- and far-field acoustic radiation. In particular, high speed impulsive noise and blade-vortex interaction are of primary interest. This paper provides an initial summary of the acoustic measurements acquired for some of the different configurations tested. A review of the baseline swept tip rotor acoustic characteristics in the regimes of high speed forward flight, where high speed impulsive noise dominates, and low speed descent, where severe blade vortex interaction noise occurs, is presented. The trends of these primary noise sources are studied as the first step in validating the data for release and application.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Acoustic Results of a United Technologies Scale Model Helicopter Rotor Tested at DNW


    Contributors:
    S. R. Liu (author) / M. A. Marcolini (author)

    Publication date :

    1990


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Advanced CBM Technologies for Helicopter Rotor Systems - Full Scale Rotor Demonstration and Test Results

    Andrews, J.R. / Augustin, M. / Yeary, R.D. et al. | British Library Conference Proceedings | 2010


    Aerodynamic and acoustic test of a United Technologies model scale rotor at DNW

    Yu, Yung H. / Liu, Sandy R. / Jordan, Dave E. et al. | NTRS | 1990