### Abstract

Aerodynamic noise from a landing gear in a uniform flow is computed using the Ffowcs Williams-Hawkings (FW-H) equation. The time accurate flow data on the surface is obtained using a finite volume flow solver on an unstructured grid. The FW-H equation is solved using surface integrals over the landing gear surface and over a permeable surface away from the landing gear. Two geometric configurations are tested in order to assess the impact of two lateral struts on the sound level and directivity in the far-field. Predictions from the FW-H code are compared with direct calculations by the flow solver at several observer locations inside the computational domain. The permeable FW-H surface predictions match those of the flow solver in the near-field. Far-field noise calculations coincide for both integration surfaces. The increase in drag observed between the two landing gear configurations is reflected in the sound pressure level and directivity mainly in the streamwise direction.

Original language | English (US) |
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Title of host publication | 40th AIAA Aerospace Sciences Meeting and Exhibit |

State | Published - 2002 |

Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: Jan 14 2002 → Jan 17 2002 |

### Other

Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
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Country | United States |

City | Reno, NV |

Period | 1/14/02 → 1/17/02 |

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### All Science Journal Classification (ASJC) codes

- Space and Planetary Science
- Aerospace Engineering

### Cite this

*40th AIAA Aerospace Sciences Meeting and Exhibit*

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*40th AIAA Aerospace Sciences Meeting and Exhibit.*40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States, 1/14/02.

**Landing gear aerodynamic noise prediction using unstructured grids.** / Souliez, Frederic J.; Long, Lyle Norman; Morris, Philip John; Sharma, Anupam.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

TY - GEN

T1 - Landing gear aerodynamic noise prediction using unstructured grids

AU - Souliez, Frederic J.

AU - Long, Lyle Norman

AU - Morris, Philip John

AU - Sharma, Anupam

PY - 2002

Y1 - 2002

N2 - Aerodynamic noise from a landing gear in a uniform flow is computed using the Ffowcs Williams-Hawkings (FW-H) equation. The time accurate flow data on the surface is obtained using a finite volume flow solver on an unstructured grid. The FW-H equation is solved using surface integrals over the landing gear surface and over a permeable surface away from the landing gear. Two geometric configurations are tested in order to assess the impact of two lateral struts on the sound level and directivity in the far-field. Predictions from the FW-H code are compared with direct calculations by the flow solver at several observer locations inside the computational domain. The permeable FW-H surface predictions match those of the flow solver in the near-field. Far-field noise calculations coincide for both integration surfaces. The increase in drag observed between the two landing gear configurations is reflected in the sound pressure level and directivity mainly in the streamwise direction.

AB - Aerodynamic noise from a landing gear in a uniform flow is computed using the Ffowcs Williams-Hawkings (FW-H) equation. The time accurate flow data on the surface is obtained using a finite volume flow solver on an unstructured grid. The FW-H equation is solved using surface integrals over the landing gear surface and over a permeable surface away from the landing gear. Two geometric configurations are tested in order to assess the impact of two lateral struts on the sound level and directivity in the far-field. Predictions from the FW-H code are compared with direct calculations by the flow solver at several observer locations inside the computational domain. The permeable FW-H surface predictions match those of the flow solver in the near-field. Far-field noise calculations coincide for both integration surfaces. The increase in drag observed between the two landing gear configurations is reflected in the sound pressure level and directivity mainly in the streamwise direction.

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M3 - Conference contribution

AN - SCOPUS:78149447164

BT - 40th AIAA Aerospace Sciences Meeting and Exhibit

ER -