Piezo-sensors for in-situ boundary layer monitoring on morphing wings

Development, validation and implementation

Doctoral thesis (2021)

Authors

V.L. Stuber Novel Aerospace Materials - Aerospace Engineering
Research Group
Novel Aerospace Materials (Aerospace Engineering) (TU Delft)
Copyright: © 2021 V.L. Stuber
DOI: https://doi.org/10.4233/uuid:88181e83-edb5-4ed1-ae02-de119786ffbb
Sensors Piezoelectricmaterials Laminar-to-turbulent transition
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Published Date

2021

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Novel Aerospace Materials

Abstract

This thesis describes the development, validation and implementation of piezoelectric flow sensors. These sensors are meant to measure flow phenomena such as transition and separation in the boundary layer of an aircraft wing. Such information can be used
as input variables to a control loop to push laminar-to-turbulent transition towards the trailing edge of a wing, thereby reducing the overall skin friction drag. The developed sensors are installed in the SmartX wing, which is a morphing wing developed at the
Delft University of Technology (TUD).