Searched for: author%3A%22Serpieri%2C+J.%22
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document
Rizzo, Paolo (author), Serpieri, J. (author), Kotsonis, M. (author)
The present work is an experimental investigation of stationary crossflow (CF) instability-induced transition of the boundary layer over a 45°swept wing, under varying free-stream turbulence, surface roughness, angle of attack and Reynolds number. Key topological features of the transition front, such as the mean transition location and the...
conference paper 2019
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Groot, K.J. (author), Serpieri, J. (author), Pinna, Fabio (author), Kotsonis, M. (author)
A combined experimental and numerical approach to the analysis of the secondary stability of realistic swept-wing boundary layers is presented. Global linear stability theory is applied to experimentally measured base flows. These base flows are three-dimensional laminar boundary layers subject to spanwise distortion due to the presence of...
journal article 2018
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Serpieri, J. (author), Kotsonis, M. (author)
In this study, experiments are performed towards the identification and measurement of unsteady modes occurring in a transitional swept wing boundary layer. These modes are generated by the interaction between the primary stationary and travelling cross-flow instabilities or by secondary instability mechanisms of the stationary cross-flow...
journal article 2018
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Yadala, Srikar (author), Hehner, M.T. (author), Serpieri, J. (author), Benard, Nicolas (author), Dörr, Philipp C. (author), Kloker, Markus J. (author), Kotsonis, M. (author)
Control of laminar-to-turbulent transition on a swept-wing is achieved by base-flow modification in an experimental framework, up to a chord Reynolds number of 2.5 million. This technique is based on the control strategy used in the numerical simulation by Dörr & Kloker (J. Phys. D: Appl. Phys., vol. 48, 2015b, 285205). A spanwise uniform...
journal article 2018
document
Serpieri, J. (author)
The research presented in this booklet focusses on the cross-flow instability. Applying traditional and advanced flow diagnostics, the boundary layer evolution is studied in detail. The topology and evolution of both primary and secondary instability mechanisms is revealed with unprecedented detail for experimental research paving the way for...
doctoral thesis 2018
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Yadala, Srikar (author), Hehner, M.T. (author), Serpieri, J. (author), Benard, Nicolas (author), Kotsonis, M. (author)
In the present work, laminar flow control, following the discrete roughness elements (DRE) strategy, also called upstream flow deformation (UFD) was applied on a 45<sup>◦</sup> swept-wing at a chord Reynold’s number of Re<sub>c</sub> = 2.1 · 10<sup>6</sup> undergoing cross-flow instability (CFI) induced transition. Dielectric barrier...
conference paper 2018
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Serpieri, J. (author), Yadala, Srikar (author), Kotsonis, M. (author)
In the current study, selective forcing of cross-flow instability modes evolving on a swept wing at is achieved by means of spanwise-modulated plasma actuators, positioned near the leading edge. In the perspective of laminar flow control, the followed methodology holds on the discrete roughness elements/upstream flow deformation (DRE/UFD)...
journal article 2017
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Groot, K.J. (author), Serpieri, J. (author), Kotsonis, M. (author), Pinna, Fabio (author)
conference paper 2017
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Serpieri, J. (author), Kotsonis, M. (author)
Time-resolved PIV measurements of the secondary instability modes of cross-flow vortices are presented. Measurements are performed on a large scale 45o swept wing at chord Reynolds number of 2.17 million in a low turbulence wind-tunnel facility. Using acquisition frequencies of 20 kHz, the present study is the first experimental demonstration...
conference paper 2017
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Serpieri, J. (author), Kotsonis, M. (author)
An experimental investigation of primary and secondary crossflow instability developing in the boundary layer of a 45° swept wing at a chord Reynolds number of 2.17 × 10<sup>6</sup> is presented. Linear stability theory is applied for preliminary estimation of the flow stability while surface flow visualisation using fluorescent oil is...
journal article 2016
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Serpieri, J. (author), Kotsonis, M. (author)
In this work the flow visualization of the transition pattern occurring on a swept wing in a subsonic flow is presented. This is done by means of fluorescent oil flow technique and boundary layer hot-wire scans. The experiment was performed at Reynolds number of 2:15 . 106 and at angle of attack of -3º. At these conditions, three different flows...
conference paper 2015
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Pröbsting, S. (author), Serpieri, J. (author), Scarano, F. (author)
The present study investigates the mechanisms associated with tonal noise emission from a NACA 0012 aerofoil at moderate incidence (0; 1; 2 and 4 angle of attack) and with Reynolds numbers ranging from 100 000 to 270 000. Simultaneous time-resolved particle image velocimetry (PIV) of the aeroacoustic source region near the trailing edge and...
journal article 2014
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Pröbsting, S. (author), Serpieri, J. (author), Scarano, F. (author)
Tonal noise generated by airfoils observed at low to moderate Reynolds numbers is related to laminar boundary layer instabilities, which has lead to the term laminar boundary layer instability noise. The particular features of the acoustic spectrum have been discussed and a number of theories have been proposed in literature over the past 50...
conference paper 2013
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Pröbsting, S. (author), Serpieri, J. (author), Scarano, F. (author)
Tonal noise generated by airfoils observed at low to moderate Reynolds numbers is related to laminar boundary layer instabilities, which has lead to the term laminar boundary layer instability noise. The particular features of the acoustic spectrum have been discussed and a number of theories have been proposed in literature over the past 50...
conference paper 2013
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