Deterministic and statistical analysis of trailing-edge noise mechanisms with and without serrations

G. Romani, Wouter C.P. Van Der Velden, Damiano Casalino

Research output: Chapter in Book/Conference proceedings/Edited volumeConference contributionScientificpeer-review

5 Citations (Scopus)


The scope of this paper is to perform a detailed analysis of the unsteady flow properties in proximity of the trailing-edge of a lifting free transition NACA 64-618 extruded airfoil. The natural transition cases 6 and 7 of the AIAA workshop on Benchmark Problems for Airframe Noise Computations (BANC-V Category 1) are considered as references. The numerical flow solution is carried out by using the fully explicit, transient and compressible lattice-Boltzmann equation implemented in the CFD/CAA solver Exa PowerFLOWR. The acoustic far-field is obtained by using the Ffowcs-Williams and Hawking integral solution applied to the wing surface. In addition, the validity of Roger and Moreau's trailing- edge model, fed with Schlinker-Amiet's and Rozenberg's wall-pressure spectrum model, is checked by comparison with both experimental and numerical results. The influence of the computational grid on the turbulent boundary layer statistics at the trailing-edge is documented as well. As conclusive effort, the effectiveness of sawtooth serrations on noise reduction is investigated by considering two different flap angles at a fixed airfoil incidence.

Original languageEnglish
Title of host publication2018 AIAA/CEAS Aeroacoustics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages16
ISBN (Electronic)9781624105609
Publication statusPublished - 1 Jan 2018
EventAIAA/CEAS Aeroacoustics Conference, 2018 - Atlanta, United States
Duration: 25 Jun 201829 Jun 2018


ConferenceAIAA/CEAS Aeroacoustics Conference, 2018
Country/TerritoryUnited States


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