Direct simulation of acoustic scattering by a rotorcraft fuselage

Anurag Agarwal, Philip J. Morris

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

A new technique is used to simulate the scattering of sound by a rotorcraft fuselage. In this technique, the scattering body is replaced by a region of different acoustic impedance. The main rotor is taken to be the noise source and is modeled by a rotating dipole. The linearized Euler equations are solved to get the near-field noise. The far-field noise is obtained by a numerical integration of the Ffowcs Williams-Hawkings equation in the near-filed. Comparisons are made between the noise levels obtained by the solution of these equations in the presence and in the absence of the fuselage. It is observed that both the near-field and far-field noise levels are significantly altered due to the presence of the scattering fuselage.

Original languageEnglish (US)
StatePublished - Dec 1 2000
Event6th Aeroacoustics Conference and Exhibit, 2000 - Lahaina, HI, United States
Duration: Jun 12 2000Jun 14 2000

Other

Other6th Aeroacoustics Conference and Exhibit, 2000
CountryUnited States
CityLahaina, HI
Period6/12/006/14/00

Fingerprint

rotary wing aircraft
fuselages
acoustic scattering
Fuselages
Acoustics
Scattering
Acoustic impedance
simulation
Euler equations
far fields
near fields
Ffowcs Williams-Hawkings equation
scattering
Rotors
Acoustic waves
acoustic impedance
numerical integration
rotors
dipoles
acoustics

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Acoustics and Ultrasonics

Cite this

Agarwal, A., & Morris, P. J. (2000). Direct simulation of acoustic scattering by a rotorcraft fuselage. Paper presented at 6th Aeroacoustics Conference and Exhibit, 2000, Lahaina, HI, United States.
Agarwal, Anurag ; Morris, Philip J. / Direct simulation of acoustic scattering by a rotorcraft fuselage. Paper presented at 6th Aeroacoustics Conference and Exhibit, 2000, Lahaina, HI, United States.
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Agarwal, A & Morris, PJ 2000, 'Direct simulation of acoustic scattering by a rotorcraft fuselage' Paper presented at 6th Aeroacoustics Conference and Exhibit, 2000, Lahaina, HI, United States, 6/12/00 - 6/14/00, .

Direct simulation of acoustic scattering by a rotorcraft fuselage. / Agarwal, Anurag; Morris, Philip J.

2000. Paper presented at 6th Aeroacoustics Conference and Exhibit, 2000, Lahaina, HI, United States.

Research output: Contribution to conferencePaper

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T1 - Direct simulation of acoustic scattering by a rotorcraft fuselage

AU - Agarwal, Anurag

AU - Morris, Philip J.

PY - 2000/12/1

Y1 - 2000/12/1

N2 - A new technique is used to simulate the scattering of sound by a rotorcraft fuselage. In this technique, the scattering body is replaced by a region of different acoustic impedance. The main rotor is taken to be the noise source and is modeled by a rotating dipole. The linearized Euler equations are solved to get the near-field noise. The far-field noise is obtained by a numerical integration of the Ffowcs Williams-Hawkings equation in the near-filed. Comparisons are made between the noise levels obtained by the solution of these equations in the presence and in the absence of the fuselage. It is observed that both the near-field and far-field noise levels are significantly altered due to the presence of the scattering fuselage.

AB - A new technique is used to simulate the scattering of sound by a rotorcraft fuselage. In this technique, the scattering body is replaced by a region of different acoustic impedance. The main rotor is taken to be the noise source and is modeled by a rotating dipole. The linearized Euler equations are solved to get the near-field noise. The far-field noise is obtained by a numerical integration of the Ffowcs Williams-Hawkings equation in the near-filed. Comparisons are made between the noise levels obtained by the solution of these equations in the presence and in the absence of the fuselage. It is observed that both the near-field and far-field noise levels are significantly altered due to the presence of the scattering fuselage.

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Agarwal A, Morris PJ. Direct simulation of acoustic scattering by a rotorcraft fuselage. 2000. Paper presented at 6th Aeroacoustics Conference and Exhibit, 2000, Lahaina, HI, United States.