06 Fakultät Luft- und Raumfahrttechnik und Geodäsie
Permanent URI for this collectionhttps://elib.uni-stuttgart.de/handle/11682/7
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Item Open Access The near-wake development of a wind turbine operating in stalled conditions : part 1: assessment of numerical models(2024) Weihing, Pascal; Cormier, Marion; Lutz, Thorsten; Krämer, EwaldThis study comprehensively investigates the near-wake development of a model wind turbine operating at a low tip-speed ratio in stalled conditions. In the present paper, part 1, different ways of representing the turbine, which include a full geometrical representation and modeling by means of the actuator line method, and different approaches for the modeling of turbulence are assessed. The simulation results are compared with particle image velocimetry (PIV) measurements from the MEXICO and New MEXICO experiments. A highly resolved numerical setup was created and a higher-order numerical scheme was applied to target an optimal resolution of the tip vortex development and the wakes of the blades. Besides the classical unsteady Reynolds-averaged methodology, a recently developed variant of the detached-eddy simulation (DES) was employed, which features robust shielding capabilities of the boundary layers and enhanced transition to a fully developed large-eddy simulation (LES) state. Two actuator line simulations were performed in which the aerodynamic forces were either evaluated by means of tabulated data or imposed from the averaged blade loads of the simulation with full blade geometry. The purpose is to distinguish between the effects of the force projection and the force calculation in the underlying blade-element method on the blade wake development. With the hybrid Reynolds-averaged Navier-Stokes (RANS)-LES approach and the geometrically fully resolved rotor blade, the details of the flow of the detached blade wake could be resolved. The prediction of the wake deficit also agreed very well with the experimental data. Furthermore, the strength and size of the blade tip vortices were correctly predicted. With the linear unsteady Reynolds-averaged Navier-Stokes (URANS) model, the wake deficit could also be described correctly, yet the size of the tip vortices was massively overestimated. The actuator line method, when fed with forces from the fully resolved simulation, provides very similar results in terms of wake deficit and tip vortices to its fully resolved parent simulation. However, using uncorrected two-dimensional polars shows significant deviations in the wake topology of the inner blade region. This shows that the application in such flow conditions requires models for rotational augmentation. In part 2 of the study, to be published in another paper, the development and the dynamics of the early tip vortex formation are detailed.Item Open Access Optimizing automated postprocessing of point clouds for accurate wind turbine blade CFD analysis(2024) Schollenberger, KaiItem Open Access Experiments on laminar separation bubbles under inflow conditions of atmospheric turbulence(2024) Greiner, Michael; Krämer, Ewald (Prof. Dr.-Ing.)Natural laminar flow (NLF) airfoils have been largely responsible for the performance advances of today's general aviation aircraft and wind turbines. In the design of these airfoils, atmospheric turbulence has received little attention, although specific atmospheric conditions are often present during their operation. One reason for this is that the effect of atmospheric turbulence on the boundary layer, and in particular on laminar separation bubbles (LSB), has only been possible to be estimated from experience. This study addresses this issue based on the example of sailplanes. In the first part of this work, the inflow conditions during typical cross-country flights of sailplanes are studied. Avoiding laminar separation bubbles at high lift coefficients is one of the challenges in the design of NLF airfoils. Therefore, the focus is on circling in thermals and thus on the convective boundary layer of the atmosphere. Continuous measurements of free-stream turbulent velocity fluctuations have been made during cross-country flights, with resolutions well into the dissipation range of the turbulence spectrum. The second part studies the effect of free-stream turbulence on mid-chord laminar separation bubbles that may appear on the upper surface of low speed NLF airfoils typically used in general aviation or wind turbines. For this purpose, the relevant conditions found in the first part were transferred to the Laminar Wind Tunnel (Re = 880,000, Tu = 0.01%-0.38%) for detailed experimental investigation. A distinction is made between small-scale turbulence, which acts via the classical vortex receptivity, and large-scale turbulence, which corresponds to inflow angle fluctuations and acts on the evolution of the boundary layer via the transient change in stability properties. The insights gained in flight permit the modelling of the free stream turbulence to be expected in flight through the convective atmosphere. The results of the wind tunnel experiments allow to better regard these turbulent conditions during the design of NLF airfoils.Item Open Access Numerical wind potential analysis in urban environments(2024) Grün, Maximilian von der; Krämer, Ewald (Prof. Dr.-Ing.)Item Open Access Experimental investigations on the flow over a complex topography in boundary layer wind tunnels(2024) Peters, Bernd; Krämer, Ewald (Prof. Dr.-Ing.)In zwei Grenzschichtwindkanälen des Instituts wurde das Geschwindigkeitsfeld über einer komplexen Topographie experimentell vermessen. Dabei handelt es sich um ein Landschaftsmodell des Albaufstiegs nahe Schnittlingen (Donzdorf, Landkreis Göppingen) im Maßstab von 1:400 bzw. 1:1200.Item Open Access A systematic DNS approach to isolate wall-curvature effects in spatially developing boundary layers(2024) Appelbaum, Jason; Kloker, Markus; Wenzel, ChristophA methodology to numerically assess wall-curvature effects in boundary layers is introduced. Wall curvature, which directly induces streamline curvature, is associated with several changes in boundary-layer flow. By necessity, a local radial pressure gradient emerges to balance mean flow turning. Moreover, a streamwise (wall-tangential) pressure gradient can appear for configurations with non-constant wall curvature or a particular freestream condition; zero pressure gradient is a special case. In laminar concave flow, the Görtler instability and the associated Taylor-Görtler vortices destabilize the flow and promote laminar-turbulent transition, whereas in the fully turbulent regime, unsteady coherent structures formed by the centrifugal instability mechanism dramatically redistribute turbulent shear stress. One difficulty of assessing centrifugal effects on boundary layers is that they often appear simultaneously with other phenomena, such as a streamwise pressure gradient, making their individual evaluation often ambiguous. For numerical studies of transitional and turbulent boundary layers, it is therefore beneficial to understand the interactive nature of such coupled effects for generic configurations. A methodology to do so is presented, and is verified using the case of a subsonic, compressible turbulent boundary layer. Four direct numerical simulations have been computed, forming a 2×2matrix of turbulent boundary-layer states; namely with and without concave wall curvature, each having a zero and a non-zero streamwise-pressure-gradient realization. The setup and accompanying procedures to determine appropriate boundary conditions are discussed, and the methodology is evaluated through analysis of the mean flow fields. Differences in mean flow properties such as wall shear stress and boundary-layer thickness due to either streamwise pressure gradient or wall curvature are shown to be remarkably independent of one another.Item Open Access Experimental investigation on boundary-layer streaks induced by grid-generated free-stream turbulence in a water channel(2024) Römer, Tristan M.; Kloker, Markus J.; Rist, Ulrich; Wenzel, ChristophIn this study, the influence of various turbulence-grid configurations is analysed on both the induced free-stream turbulence (FST) and the resulting Klebanoff modes/streaks developing in a laminar flat-plate boundary layer downstream in a laminar water channel. All results are based on hot-film and particle image velocimetry measurements as well as visualizations. The grid design and installation has been done according to common grid installation recommendations to ensure homogeneous FST causing meandering Klebanoff modes inside the boundary layer. But it was found that (i) the Klebanoff modes do not meander for all grid configurations, (ii) not all configurations cause Klebanoff modes with the expected temporal and spatial behaviour, and (iii) for some configurations, the spanwise streak spacing is strictly locked to the grid spacing (mesh width). As these observations are unreported in the literature, this study is aimed at a thorough description of the influence of key grid parameters on the FST and the resulting streaks within the boundary layer. The investigation includes the grid parameters typically reported, such as the grid-bar diameters, the associated Reynolds numbers, or the streamwise placement of the grid, but now also the grid-orientation order (horizontal/vertical or vertical/horizontal order of grid bars of the dual-plane grid), the wall-normal position of the horizontal bars relative to the leading edge of the flat plate, and the existence of palpable imperfections in the manufactured grids. The Reynolds-number range covered lies well in the lower band of wind-tunnel experiments. Thus, this study suggests that the reliability and reproducibility of future experimental studies on FST would be greatly improved if they demonstrated homogeneity in the free-stream in both spanwise and wall-normal directions, documented the ongoing meandering and wavelengths of the generated Klebanoff modes and thus (implicitly) documented the spanwise independence of the results in the temporal mean. The latter is a prerequisite for the reliable investigation of FST/isolated-roughness interactions.Item Open Access Study on constraining turbulence to met mast data from the WINSENT complex terrain test site for use as inflow for CFD simulations(2025) Müller, CarstenThis work presents a method for generating time-resolved, three-dimensional turbulent inflow conditions for URANS/DDES simulations using the flow solver FLOWer. Turbulent inflow fields are generated using the Mann Turbulence Model via python’s Hipersim package and are applied as boundary conditions in the solver. The inflow is to reproduce both the absolute values and spectral characteristics of single-point time series and 3D velocity fields represented in atmospheric turbulence. A dedicated toolchain, InFlow, was developed to process and adapt turbulence input data from the WINSENT test site near Stötten, Germany. The approach is designed to be computationally efficient, straightforward to apply, and accurate enough for use in practical wind energy simulations. Its performance and limitations are evaluated across varying inflow scenarios and setups.Item Open Access Aerodynamic interactions between distributed propellers and the wing of an electric commuter aircraft at cruise conditions(2024) Schollenberger, Michael; Kirsch, Bastian; Lutz, Thorsten; Krämer, Ewald; Friedrichs, JensBeneficial interactions that occur between propellers and the wing can be used to increase the overall efficiency of an aircraft in cruise flight. Different concepts with such interacting propellers are distributed propulsion (DP) and wingtip mounted propellers (WTP). For DP, a full distribution over the entire span can be distinguished from a partial distribution, concentrating the propellers at the wing tip area. The paper focuses on the energy efficiency in cruise flight as a result of the interactions and provides a general comparison of the concepts (WTP, full and partial DP) with a Beechcraft 1900D commuter aircraft as a reference. Parametric CFD studies varying the number and the position of the propellers are performed with a half-wing model. The simulations are performed with the second-order finite-volume flow solver TAU, developed by the German Aerospace Center (DLR), employing Reynolds-averaged Navier-Stokes (RANS) equations. The propellers are modeled using an Actuator Disk (ACD). An algorithm is used to reach cruise condition by iteratively adjusting the propeller rotational speed and the wing angle of attack. The CFD results are analyzed and evaluated with respect to the overall efficiency including the aerodynamic efficiency of the wing as well as the propulsive efficiency of the propellers. The parameter study shows that in cruise flight partial DP is more efficient than a full DP. The pure WTP configuration was found as the optimum of the propeller distribution along the wing, resulting in a saving of required power of 5.6%, relative to the reference configuration.Item Open Access Unsteady nonlinear lifting line model for active gust load alleviation of airplanes(2024) Beyer, Yannic; Ullah, Junaid; Steen, Meiko; Hecker, PeterActive gust load alleviation is an important technology for designing future passenger airplanes to be lighter and thus more environmentally friendly. Unsteady Reynolds-averaged Navier-Stokes (URANS) simulations are typically used to accurately calculate gust loads, but because of their high computational cost, they can only be performed at a few selected operating points. In simpler potential theory models, stall is neglected, resulting in loss of accuracy. In this paper, a low-order unsteady aerodynamics wing model is presented, which is able to represent well compressible flow with stall. Furthermore, the model offers the possibility to modularly incorporate actuators, which allows the design and evaluation of active load alleviation systems. The model is based on a conventional unsteady 2D airfoil model including a dynamic stall model. The dynamic stall model requires viscous steady coefficients, e.g. from 2D steady RANS computations. This 2D airfoil model is coupled with a 3D steady-state lifting line model. The model is applied to the LEISA research airplane and extensively validated with URANS results. It performs well in calculating gust loads with and without simultaneous flap deflections, and provides significantly more accurate results in the case of stall than when stall is neglected.