Abstract
Experimental study of the structure of the boundary layer on the suction side of a plate is to be presented. The flat plate with rounded edges and angle of attack of 7° is used. The boundary layer flow will be explored using the time-resolved PIV technique, measuring plane was located very close to the wall. Analysis of the flow dynamics is to be presented using the POD technique applied on both velocity and vorticity fields.
Highlights
The presented study is motivated by new ideas about principle of flight by Hoffman and Johnson from KTH Stockholm, see [1,2]
The study [3] was focused on structure of the wake behind the plate, the presented study concentrates on structure of the flow close to the suction surface of the plate
Flat plate inclined with angle of attack (AOA) 7 degrees has been placed in a uniform low turbulence stream
Summary
The presented study is motivated by new ideas about principle of flight by Hoffman and Johnson from KTH Stockholm, see [1,2]. They formulated the new hypothesis of physical mechanism of flight which relies on existence of streamwise vortical structures on the suction side of the airfoil. For the measurements, the frequency 1 kHz and 4000 double-snaps in sequence corresponding to 4 s of record for mean evaluation was acquired. The plane of measurement has been located parallel to the plate suction surface in the distance 1 mm above the surface – see Fig. 1
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