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Different methods to detect boundary layer transition are investigated within the scope of this paper. Laminar and turbulent boundary layers exhibit a significantly different behavior, not only regarding skin friction but also for heat-transfer which affects the blade cooling design. The present work presents a novel and non-intrusive measurement technique to detect the transition, based on acoustic concepts. The reliability of the technique was investigated by means of boundary layer measurements over a flat plate in subsonic flow conditions. After a preliminary assessment with a conventional Preston tube, a row of microphones were installed along the plate to correlate transition pressure fluctuations. To provide a comprehensive representation of the experiment, dedicated measurements with a fast response aerodynamic pressure probe were performed to determine the turbulence intensity and the dissipation rate upstream of the flat plate. The experimental results were systematically compared with calculations performed with three different computational fluid dynamics solvers (ANSYS-Fluent, ANSYS-CFX, OpenFOAM) and using both the and the transition models. Results show a fair agreement between CFD (computational fluid dynamics) predictions and the acoustic technique, suggesting that this latter might represent an interesting alternative option for transition measurements.

An Investigation of Innovative Experimental and Numerical Techniques to Detect Boundary Layer Transition