The structure of turbulent flow behind the NACA 0012 airfoil at high angles of attack and low Reynolds number

This paper shows the results of a study of the turbulent structure behind the NACA 0012 airfoil. During the experiment, the flow velocity was 20 m.s(-1). That corresponds the Reynolds number 1.3.10(5). The point behind the trailing edge was chosen for experimental studies. Measurements were performed at six angles of attack alpha = 0 degrees, 15 degrees, 30 degrees, 45 degrees, 60 degrees, 75 degrees and various cases of positioning the measuring section. Namely at a constant cross-section and a constant distance behind the airfoil. The NetScanner pressure system and hot-wire technique were used for experimental studies. The obtained data allowed us to investigate the wake topology. The average velocity and standard deviation distributions are clearly grouped depending on the angle of attack. Thus, flowing around the airfoil is better up to alpha <= 15 degrees. Distributions by power density and dissipation spectra also have a similar grouping tendency. Finally, we investigated the turbulent structure according to the research program. We found that at alpha >= 45 degrees, depending on the measurement case, there is a clear difference in the distribution of standard deviation, Eulerian length scale, Taylor micro-scale, and Reynolds number based on the Taylor micro-scale. The obtained values at the constant distance, in contrast to the constant cross-section, are reduced.