This paper presents the results of a series of wind tunnel tests on aerodynamic interaction between the rotor and the fuselage. A model rotor test stand IMRTS (JAXA Multi-purpose Rotor Test System) has been used to obtain time-averaged and ensemble-averaged data such as pressure on the blades and fuselage, rotor forces and moments. The blade motions were also calibrated in terms of the collective pitch, flapping and lead-lag angles under both hovering and forward flight conditions. The fuselage of JMRTS is designed after a typical helicopter shape. In the hover cases, it was confirmed that when the rotor thrust was increased, fluctuations on the fuselage increased in amplitude, with the downwash intensified. Moreover, it was spotted in the forward flight cases that time-average pressure distribution measured along a crossline of the fuselage is so asymmetric that the pressure on the retreating side is lower than that on the advancing side. Furthermore, the authors underpinned that the average pressure measured on the fuselage was expressly subject to the rotor downwash when the advance ratio was less than 0.1, while it appeared less affected when the advance ratio was more than 0.1. Consequently, an experimental database, which shall be disclosed to the public for validating CFD codes, was successfully established.


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    Titel :

    JAXA Research and Development Report, August 2010


    Erscheinungsdatum :

    2010


    Format / Umfang :

    44 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







    JAXA

    Uchū-Kōkū-Kenkyū-Kaihatsu-Kikō | TIBKAT | 2003-2005 ; damit Erscheinen eingestellt


    Microgravity Research Projects in JAXA

    Yamamoto, Shin / Yoda, Shinichi | AIAA | 2005