Vorticity statistics in the near wake of asymmetric prismatic airfoil NACA 64-618 at negative angle of attack –10° at Reynolds numbers 1.6 ⋅ 104 and 1.6 ⋅ 105 in distance 0.0 – 0.4 × chord past trailing edge measured by Particle Image Velocimetry

0575050 - ÚT 2024 FR eng C - Konferenční příspěvek (zahraniční konf.)
Narovec, J. - Duda, D. - Horáček, V. - Tomášková, T. - Uruba, Václav - Yanovych, Vitalii
Vorticity statistics in the near wake of asymmetric prismatic airfoil NACA 64-618 at negative angle of attack –10° at Reynolds numbers 1.6 ⋅ 104 and 1.6 ⋅ 105 in distance 0.0 – 0.4 × chord past trailing edge measured by Particle Image Velocimetry.
MATEC Web of Conferences. Vol. 367. Grenoble: EDP Sciences, 2022, č. článku 00017. E-ISSN 2261-236X.
[Conference on Power System Engineering /21./. Pilsen (CZ), 07.09.2022-09.09.2022]
Institucionální podpora: RVO:61388998
Klíčová slova: airfoil * vorticity * partocle image velocimetry
Obor OECD: Applied mechanics
https://www.matec-conferences.org/articles/matecconf/pdf/2022/14/matecconf_pse22_00017.pdf

The airfoil NACA 64-618 is realized by using two levels of quality: first the theoretical profile is printed on a 3D printer in a direct, “naive” way, this geometry has been scanned by using 3D scanner and based on the deviations, a better model has been processed. The flow within the turbulent wake is measured by using Particle Image Velocimetry (PIV) technique at two velocities separated by one order of magnitude.
Trvalý link: https://hdl.handle.net/11104/0350877