Volume 36 Issue 3
Mar.  2021
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YUAN Mingchuan, LI Shangbin, JIANG Lusheng. Acoustic test and numerical analysis of tilt rotor in hover[J]. Journal of Aerospace Power, 2021, 36(3): 520-529. doi: 10.13224/j.cnki.jasp.2021.03.008
Citation: YUAN Mingchuan, LI Shangbin, JIANG Lusheng. Acoustic test and numerical analysis of tilt rotor in hover[J]. Journal of Aerospace Power, 2021, 36(3): 520-529. doi: 10.13224/j.cnki.jasp.2021.03.008
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Acoustic test and numerical analysis of tilt rotor in hover

doi: 10.13224/j.cnki.jasp.2021.03.008

  • Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Aviation Industry Corporation of China Limited,Jingdezhen Jiangxi 333001,China

  • Received Date: 2020-07-11
  • Publish Date: 2021-03-28
    Abstract
  • The aeroacoustic characteristics of tilt rotor in hover were investigated based on acoustic test and numerical computation. The test was conducted with isolate model tilt rotor, and the acoustic data of different collective pitch angles and blade tip Mach number were measured. The numerical computation was made based on CFD (computational fluid dynamic) and FW-H(Ffowcs Williams-Hawkings) equation, and the calculation accuracy was validated by test data. The acoustic results of different observation positions were compared, the effects of thrust coefficients and blade tip Mach number on tilt rotor noise were analyzed, and the acoustic characteristics of isolate rotor and dual rotors were calculated. Results showed that, the overall sound pressure level of tilt rotor increased with thrust coefficients and blade tip Mach number, the decrease of tilt rotor blade tip Mach number can reduce overall sound pressure level although the thrust coefficient was increased to maintain rotor lift; the acoustic directivity of dual tilt rotors was longitudinally symmetrical, the local maximum overall sound pressure level occurred at several azimuths, due to the superposition in noise radiation and aerodynamic interaction of the two rotors.

     

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