EXPERIMENTAL INVESTIGATION OF FLOW OVER A CYLINDER AND WING WITH VORTEX GENERATORS USING PIV

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dc.contributor.advisorDarlami, Kamal
dc.contributor.authorDevkota, Kshitish Chandra
dc.contributor.authorMishra, Praphul
dc.contributor.authorAdhikari, Sandip
dc.contributor.authorBanjade, Shreeju
dc.date.accessioned2024-08-13T04:59:11Z
dc.date.available2024-08-13T04:59:11Z
dc.date.issued2024-03
dc.descriptionParticle Image Velocimetry (PIV) is a non intrusive flow measurement technique used for qualitative and quantitative analysis of flow dynamics. In this study, PIV is employed to investigate flow behaviour around a circular cylinder and a wing, with and without vortex generators (VGs).
dc.description.abstractParticle Image Velocimetry (PIV) is a non intrusive flow measurement technique used for qualitative and quantitative analysis of flow dynamics. In this study, PIV is employed to investigate flow behaviour around a circular cylinder and a wing, with and without vortex generators (VGs). The research pursues dual objectives: to characterize the PIV setup using the Strouhal number (a dimensionless parameter) and to analyze flow characteristics, particularly focusing on stall conditions. Systematically, a linear actuation mechanism is developed to facilitate experimentation on both models. Image processing, conducted in PIVLab alongside the development of necessary code written in MATLAB, are incorporated for detailed analysis, with time-dependent signals transformed into the frequency domain using Fast Fourier Transform (FFT) for comprehensive evaluation. The characterization of existing PIV setup was done through three sets of experimental data using strouhal number for analysis of flow around circular cylinder. The strouhal number obtained are 0.1897, 0.1952 and 0.1952 with 3.6777 %, 0.9137 % and 0.9137 % errors respectively. Velocity field and vorticity contours were studied for the aerodynamic flow analysis of baseline wing and wing with VG at the 15 degree angle of attack. The obtained Strouhal number for wing and wing with VGs are 0.1381 and 0.1571 respectively. The comparison concludes that vortex generators energize the boundary layer above the wing and delay the flow separation
dc.identifier.urihttps://hdl.handle.net/20.500.14540/22670
dc.language.isoen
dc.publisherI.O.E
dc.subjectVortex generator
dc.subjectImage Processing
dc.subjectCircular Cylinder
dc.subjectVortex Shedding
dc.titleEXPERIMENTAL INVESTIGATION OF FLOW OVER A CYLINDER AND WING WITH VORTEX GENERATORS USING PIV
dc.typeTechnical Report
local.academic.levelOther
local.institute.titleInstitute of Engineering
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