Unsteady surface pressure measurements on trailing edge serrations based on digital MEMS microphones

Martinus P.J. Sanders, Leandro D. De Santana, Mahdi Azarpeyvand, Cornelis H. Venner

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

16 Citations (Scopus)


The physics of turbulent flow reaching the airfoil trailing edge is fundamental to the understanding of the Turbulent Boundary Layer (TBL) noise production mechanism. The experimental validation of semi-empirical and computational models requires advances in current experimental techniques and instrumentation to allow accurate determination of turbulent structures. This research investigates the applications of digital MEMS microphones embedded for the experimental determination of unsteady wall pressure in a 3D printed NACA0012 airfoil at chord-based Reynolds number 200,000<Re<700,000. The development of this experimental technique brings challenges regarding the construction since sensors and components must be miniaturized in order to maximize the sensor spatial resolution. This paper discusses the implementation of this novel wall pressure transducer. Results indicate that the proposed approach can be effectively applied to the experimental determination of near-wall turbulence structures and other flow features, which is a major step toward improved TBL noise prediction.

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

Publication series

Name2018 AIAA/CEAS Aeroacoustics Conference


ConferenceAIAA/CEAS Aeroacoustics Conference, 2018
Country/TerritoryUnited States


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