Computational study of flow incidence effects on the aeroacoustics of low blade-tip Mach number propellers

Research output: Contribution to journalArticleScientificpeer-review

1 Citation (Scopus)
10 Downloads (Pure)

Abstract

This paper presents a computational study of flow incidence effects on the aeroacoustics of a propeller operating at low blade-tip Mach numbers. The numerical flow solution is obtained by using the Lattice-Boltzmann/Very Large Eddy Simulation method, while far-field noise is computed through the Ffowcs-Williams & Hawkings' acoustic analogy applied on the propeller surface. The presence of an angular inflow leads to: (i) the radiation of tonal loading noise along the propeller axis; (ii) the increment/reduction of the sound pressure level in the region from/to which the propeller is tilted away/towards. However, contrarily to propellers operating at high blade-tip Mach numbers, the noise directivity change is found to be governed only by the rise of periodic unsteady loadings, with the modulation of the strength of the noise sources on the blade, associated to the periodic variation of the observer-source relative Mach number (in the blade reference frame), being negligible. Finally, thickness noise and turbulent boundary-layer trailing-edge noise did not show a significant directivity variation due to the propeller yaw angle change.

Original languageEnglish
Article number107275
Number of pages14
JournalAerospace Science and Technology
Volume120
DOIs
Publication statusPublished - 2022

Keywords

  • Aeroacoustics
  • Aerodynamics
  • Drone
  • Lattice-Boltzmann method
  • Propeller
  • Yaw angle

Fingerprint

Dive into the research topics of 'Computational study of flow incidence effects on the aeroacoustics of low blade-tip Mach number propellers'. Together they form a unique fingerprint.

Cite this