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Current numerical simulations investigate subsonic flow around the NREL’s S807 airfoil without an incident angle at Reynolds numbers near 2.8∙105. This work is devoted to the assessment application of various turbulence models for a numerical simulation of the formed flow around the streamlined body in commercial software ANSYS CFX. Namely, we applied Shear Stress Transport fully turbulent model (SST0, Baseline Reynolds stress model (BSL RSM) and SSG RSM for the computation of velocity deficit, degree of turbulence anisotropy, Reynolds stress components, and aerodynamic performance of the airfoil. The obtained results were validated on the basis of hot wire measurement data. Additionally, in order to validate the obtained results, a comparison with the hot-wire experimental data was also carried out. The obtained experimental and calculated data showed some differences in the wake topology. For example, in the case of hot-wire data, there is a smaller velocity deficit and a wider area of perturbation.

The shear layer (SL) of a turbulent jet is studied by using Particle Image Velocimetry (PIV) up to distance 0.2 nozzle diameters in axial × radial plane. The jet is generated by circular nozzle at Reynolds numbers 1.1·105 to 1.1·106. This range covers the transition from laminar instable SL to turbulent SL. The observed average velocity profiles are fitted by using Michalke function. This function describes both: the shear layer of tanh profile and the boundary layer formed inside the nozzle at the same time. In the second part of this contribution we show the fluctuations, their anisotropy and length-scale observing doubling in the wavelength at the transition.

This work aimed to investigate the boundary layer topology over various densities of roughness. For experiments, we used three different surface conditions comprised of rectangular elements with uniform height arranged in staggered rows and covered the entire floor of the wind tunnel. The frontal and plan solidity for each case changed, λf from 0.3 to 1.2 and λp from 1.3 to 4.7, respectively. Also, we used one more surface, without roughness, for comparison. During the experiment, the position of measuring cross-sections varied relative to the inlet, while the free flow velocity was 5 m·s-1. Thus, the corresponding Reynolds number Reτ was from 300 to 1500 (based on boundary layer thickness δ and friction velocity uτ) or Reθ was from 400 to 5500 (based on momentum thickness). To determine the boundary layer topology in streamwise directions, we used a 55P14 miniature hot-wire probe. The obtained data allowed us to estimate patterns of distribution mean velocity profile, streamwise Reynolds stress, and turbulence intensity for different surface cases. In addition, an analysis of the scales of the turbulent flow over different surface types was also carried out. Namely, the integral length scale, Taylor microscale, and dissipation scale were determined. Obtained results show that roughness density composition strongly affects boundary layer characteristics. The obtained results also represent a correlation between the Taylor microscale and the initial position of the log region.

The electricity industry plays an irreplaceable role in the rise of the economic potential and development of every country around the world. The international community of industry, research institutions and global businesses focuses more on green finance; it rises its interest in environmental protection, climate change and strategies for sustainable development. A worldwide sudden increase in electricity consumption could occur due to the commitment to decarbonize economies. The implementation of an energy audit and its control elements in energy management is of great benefit to the organization and leads to the rational use of energy resources and improvement of energy efficiency. In addition, it can also promote the continuous sustainable development of the economy and society. Therefore, it seems reasonable for the electric power industry to incorporate the principles of sustainable development into its strategy and operations. This study aims to evaluate the energy audit and its impact on the environment in the context of reviewing current and potential problems and prospects. It will also describe the role of renewable energy in the sustainable development of the electricity sector. Furthermore, it identifies the main factors of sustainable development for the electricity sector.

The effect of leading edge erosion to the flow is studied experimentally by standard method of Particle Image Velocimetry. Three airfoil models are manufactured: the reference one, the homogenously eroded one, which is modeled by putting a sheet of sand-paper to its leading edge and the airfoil with large erosion, which is modeled by regular spikes and a valley in sub-stagnation area. The damaged airfoils support earlier transition to turbulence; in fully turbulent regime, their wake is wider than in the smooth case and, especially in the case of regular spikes, the spanwise fluctuations are reduced.

The primary goal of this investigation was to analyze the specific evolution of the boundary layer over an isolated roughness. A specific surface consisting of rectangular elements of the same height arranged in a checkerboard pattern was used for the experiments. Throughout the experiment, the measuring cross-sections were positioned at various distances from the inlet, while maintaining a constant flow velocity of 15 m·s-1. To investigate the boundary layer topology in the streamwise directions, a 55P14 miniature hot-wire probe was employed. It is worth mentioning that the measuring position was situated at the midpoint between the roughness elements. Through the analysis of the gathered data, we identified the distribution patterns of the mean velocity profile at different measuring positions. Additionally, we estimated the integral scale of the turbulence by applying different approaches, such as the zero-crossing method (based on autocorrelation analysis), and the Roach and Karman methods (based on spectral density function). The data obtained from our experiments demonstrate that the presence of isolated roughness leads to a pronounced alteration of the velocity profile. This phenomenon is likely due to the shear layer, which typically contains the largest and most energetic vortices in the flow.

The canonical case of a circular cylinder in crossflow is studied experimentally at Reynolds number 5k. The power-spectra of all velocity components in the turbulent wake are studied in detail. Special attention is paid to the appearance of peaks and spectra shape, i.e., to the slope of spectra parts. Signatures of presence forward energy cascade and inverse enstrophy cascade are detected. Three peaks corresponding to 1st, 2nd and 3rd harmonics of the Strouhal frequency are detected as well as local spectra slopes conforming to the Kolmogorov and Kraichnan theories.

A system of stream-wise vortices has been created using a grid of swirling elements with alternating orientations (like a chessboard). The particle image velocimetry method has been used to map the velocity field in several planes perpendicular to the stream. The mesh-based Reynolds number is 1.35 × 10 4 and 2.71 × 10 4 , respectively. The stream-wise development of turbulent kinetic energy (TKE) shows first an increase in a distance of x ≈ 10 M , followed by power-law decay. Individual vortices are detected in each snapshot. The radial profile of TKE transformed to a vortex coordinate system is almost constant, either with maximum as in static frame or zero as observed by previous research. The properties of detected vortices are studied statistically: the meandering amplitude expressed as the standard deviation of vortex positions grows roughly as ∼ e x , i.e., faster than expected random-walk growth ∼ x . Vortex circulation decays exponentially as predicted by classical Helmholtz theorem. The interaction between neighboring vortices is expressed via correlation of selected quantities. Correlation of energy develops downstream from anticorrelation to a positive correlation. The strongest correlation is observed between the first vortex circulation and the second vortex position perpendicular to their connection line. Other correlations are weak. [ABSTRACT FROM AUTHOR]

Aluminum construction profiles become a standard construction material for short-term stands in science and in industry as well. It has the shape of square prism with an groove in each side to easy connecting the nut or bolt in any location. We studied the wake past the profile of 45 mm side. We studied the topology of the wake in the dependence on the angle of attack by using the Particle Image Velocimetry technique.

We studied the grid-generated turbulence by using Particle Image Velocimetry (PIV) technique. We test on this already well studied flow the new ways of analyzing spatially resolved PIV data, such as the spatial spectra and structure functions. We compare some of the turbulence characteristics with results of Laser Doppler Anemometry (LDA).

This paper presents the results of the drag coefficient estimations for different types of NREL airfoils based on the experimental data. Namely, it was S803, S807, S813, and S817 profiles with the same chord length. The investigations were conducted at three angles of attack α=0°, α=±5°, different chord-based Reynolds numbers 0.6×105, 1.3×105 and 2.6×105. While, measuring cross-sections were placed behind the trailing edge at x∙c−1≈0.2, 0.4 and 1.0. Experimental data were collected using a hot-wire split fiber probe 55R55, which allowed us to estimate the characteristics of turbulent flow in stream-wise and crosswise directions. According to the obtained results, the highest and lowest Cd values correspond to profiles S817 and S803, respectively. Moreover, the results show that more asymmetric profiles S803 and S807 have the lowest resistance at zero angles of attack. Research background: Application of Antonia and Rajagopalan methodology to drag assessment of various stream bodies. Purpose of the article: Comparative evaluation of the drag coefficients of the NREL airfoils based on instantaneous velocity distribution behind. Methods: Hot-wire anemometry with split fiber probe 55R55. Findings & Value added: The highest drag coefficient corresponds to the S817 profile. The asymmetry of the airfoil shape has a significant impact on its drag characteristics.

The grid turbulence past a grid made of row of prismatic circular rods (rod diameter = 10 mm, rod spacing = 20 mm) perpendicular to the flow is observed by using a pair of PIV cameras. The first one has field of view larger (81 mm), the second one smaller (31 mm), which increases the dynamical range, where the spectral turbulence properties can be explored. Energy spectra displays usual behavior approximately following k −5/3 law, the anisotropy originates at larger scales and the flatness describing strong rare events is connected with smaller scales. The spectral properties of vorticity do not collapse due to the different lengthscale of differentiation, which make questionable the previous research based on the vorticity statistics. Research background: Grid turbulence is the best experimentally accessible prototype of ideal homogenous and isotropic turbulence, although it is known, it is not exactly the ideal one. Purpose of the article: This contribution explores the possibility of expanding the limited dynamical range of PIV method. Methods: Particle Image Velocimetry is based on observing the motion of small particles carried by the flow. Findings & Value added: Anisotropy connected with large scales, flatness with small scales; it does not work for vorticity.

This work aimed to investigate the turbulence characteristics behind different parts of the wind turbine blade. Airfoils S807, S813, S817, and S803, which characterize the shape of the blade at different lengths, were selected for estimation. During the experiment, the chord-based Reynolds number was 2.6×105, while the angle of attack was zero. Measuring crosssections were placed behind the trailing edge at x·c-1≈0.2, 0.4 and 1.0. For the determination flow topology, we used a Hotwire anemometry with a split fiber probe 55R55 and a miniature X-wire probe 55P64. The obtained data allowed us to determine and compare the evolution of the wake behind different types of airfoils in streamwise and spanwise directions. Thus, the largest and smallest velocity deficit located behind S817 and S803 airfoils, respectively. This trend is also evident in the Normalized Reynolds shear stress distributions. Finally, we determined the spectrum and calculated the Integral length scale, the Taylor and Kolmogorov microscale of turbulent flow. According to the results, profile S817 contributes to the formation of a flow with a large scale of turbulence, while the S803 is contrary.

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.

The feasibility study of Particle Image Velocimetry (PIV) measurements inside a test turbine at the University of West Bohemia. The current VT-400 turbine is not prepared for optical measurement with seeding particles, thus several technical issues had to be addressed until low-quality data were obtained only at low speed of 2000 RPM (rounds per minute). Even the low quality data are able to show the fluctuation anisotropy or the size of fluctuation structures, which are quantities not measurable by classical pressure methods.

The article describes a numerical simulation of flow in the cooling system of an electromagnetic calorimeter by analysing the temperature and pressure fields. Two fundamentally different approaches were used to analyse the pressure field - analytical 1D calculation and numerical 3D flow simulation. The article contains a detailed evaluation and description of individual analyses using the commercial software ANSYS 2020 R1.

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 1.3·105. The point behind the trailing edge was chosen for experimental studies. Measurements were performed at six angles of attack α = 0°, 15°, 30°, 45°, 60°, 75° and various cases of positioning the measuring section. Namely at a constant crosssection 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 α ≤15°. 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 α ≥45°, 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.

We observe that decreasing the inner nozzle surface by adding longitudinal ribs increases the jet stability in terms of the amount of turbulent kinetic energy in the near shear layer. We try to explain our observation as a stabilization effect of secondary flow vortices emerging in the corners of the ribs. These stream-wise vortices damage the development of larger-scale structures in the near shear layer. This explanation is supported by autocorrelation function of the stream-wise velocity component, which displays slightly smaller integral length-scale in the case with ribs than in the case of smooth nozzle. The experiment is performed at Reynolds number 2.2 × 105 (based on the nozzle diameter 50 mm); the Stereo-PIV (Particle Image Velocimetry) measurement takes place at the plane perpendicular to the jet axis one diameter past the nozzle exit. Optical 3D scanner controls the real nozzle geometry. This article presents preliminary measurement at single position and single velocity only; further exploration of this problem is needed.

Wind tunnels are popularly used to study various aerodynamic phenomena. Their design significantly influences the quality of the created airflow. During the flow generation, the construction parts of the wind tunnel to get deformed due to pressure variations. This phenomenon significantly complicates the creation of high-level laminar flow and worsens the results of experimental studies. The main purpose of this work is to investigate the effect of a sharp change in flow velocity on the structural stability of parts of a wind tunnel with a capacity of 55 kW. For experimental studies, we used the ARAMIS optical measurement system. Using it, we estimated the amount of deformation and mutual displacement of parts of the running wind tunnel at a flow rate of 76 m·s-1.

Particle Image Velocimetry (PIV) is an experimental method of fluid research resulting into a spatially resolved two-dimensional velocity field. We measured the velocity inside a single-stage axial test turbine at the Czech Aerospace Research Centre. We studied the axial × tangential plane just behind the rotor wheel at the tip radius under three regimes: underloaded, designed and overloaded ones. We found individual vortices in the instantaneous snapshots and we analyze their properties statistically.

We present a educational poster supporting the subject „Mechanics of fluids I“, which the students evaluate to be difficult mainly due to abstractness. Our goal is to show in vivo the behavior, especially the non-linearity, of various flows transiting into turbulence. The fluid motion is visualized by using the rheoscopic fluid, which consist of water and the dust of mica, whose particles are longitudinal and shiny resulting into easily observable reflections, when the particles coherently orient along the maximum stress. This happens mainly in shear layers, e.g. at the boundary between vortex core and envelope. An example of flow transiting into turbulence is the Taylor-Couette flow between two concentric cylinders, which with increasing Taylor number passes through various regimes from fully laminar bearing flow through the Taylor vortex flow (TVF) and later Wavy vortex flow (WVF) up to Turbulent Taylor vortices regime (TTV) and, finally, the regime of featureless turbulence.

PIV (particle image velocimetry) measurement of the air flow past a counter-swirler 53983 (anticlockwise swirler surrounded by clockwise swirler) is performed. The measurement is focused to an area at the boundary between the inner swirling jet and the outer one rotating oppositely. The Reynolds number Re based on the inner swirler diameter ranged form 1.2·103 to 2.1·104. By using band pass filtering the shear layer and vortices in the contact region between counter-swirling jets is highlighted. The shear layer between these regions shortens and decays into vortices as Reynolds number increases.