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Relevant bibliographies by topics / DLR-TAU

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Academic literature on the topic 'DLR-TAU'

Author: Grafiati

Published: 4 June 2021

Last updated: 2 February 2022

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Journal articles on the topic "DLR-TAU"

1

Stuermer, Arne. "DLR TAU-Code uRANS Turbofan Modeling for Aircraft Aerodynamics Investigations." Aerospace 6, no. 11 (November 3, 2019): 121. http://dx.doi.org/10.3390/aerospace6110121.

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In the context of an increased focus on fuel efficiency and environmental impact, turbofan engine developments continue towards larger bypass ratio engine designs, with Ultra-High Bypass Ratio (UHBR) engines becoming a likely power plant option for future commercial transport aircraft. These engines promise low specific fuel consumption at the engine level, but the resulting size of the nacelle poses challenges in terms of the installation on the airframe. Thus, their integration on an aircraft requires careful consideration of complex engine–airframe interactions impacting performance, aeroelastics and aeroacoustics on both the airframe and the engine sides. As a partner in the EU funded Clean Sky 2 project ASPIRE, the DLR Institute of Aerodynamics and Flow Technology is contributing to an investigation of numerical analysis approaches, which draws on a generic representative UHBR engine configuration specifically designed in the frame of the project. In the present paper, project results are discussed, which aimed at demonstrating the suitability and accuracy of an unsteady RANS-based engine modeling approach in the context of external aerodynamics focused CFD simulations with the DLR TAU-Code. For this high-fidelity approach with a geometrically fully modeled fan stage, an in-depth study on spatial and temporal resolution requirements was performed, and the results were compared with simpler methods using classical engine boundary conditions. The primary aim is to identify the capabilities and shortcomings of these modeling approaches, and to develop a best-practice for the uRANS simulations as well as determine the best application scenarios.

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Kirz, Jochen, and Ralf Rudnik. "DLR TAU Simulations for the Second AIAA Sonic Boom Prediction Workshop." Journal of Aircraft 56, no. 3 (May 2019): 912–27. http://dx.doi.org/10.2514/1.c034819.

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Martín, M. J., E. Andrés, M. Widhalm, P. Bitrián, and C. Lozano. "Non-uniform rational B-splines-based aerodynamic shape design optimization with the DLR TAU code." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, no. 10 (December 7, 2011): 1225–42. http://dx.doi.org/10.1177/0954410011421704.

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Franze, Marius. "Comparison of a closed-loop control by means of high-fidelity and low-fidelity coupled CFD/RBD computations." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 10 (October 16, 2019): 1611–23. http://dx.doi.org/10.1177/0954410019882275.

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This work compares the principle of a basic fin-controlled sounding rocket with coupled computational fluid dynamic and rigid body dynamic simulations of two coupling environments: (1) a low-fidelity approach using Missile DATCOM as semi-empirical aerodynamic solver, and (2) a high-fidelity approach using DLR TAU as URANS CFD code. The flight mechanics solver REENT is used in both cases. A closed-loop flight path control is developed and adjusted via low-fi simulations and then verified via high-fi simulations. For simple roll and pitching maneuvers the environments match well, whereas differences can be seen in complex maneuvers, e.g. body–body interactions of separation procedures.

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Auerswald, Torsten, Jens Bange, Tobias Knopp, Keith Weinman, and Rolf Radespiel. "Large-Eddy Simulations of realistic atmospheric turbulence with the DLR-TAU-code initialized by in situ airborne measurements." Computers & Fluids 66 (August 2012): 121–29. http://dx.doi.org/10.1016/j.compfluid.2012.06.013.

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Schütte, Andreas, and Heinrich Lüdeke. "Numerical investigations on the VFE-2 65-degree rounded leading edge delta wing using the unstructured DLR TAU-Code." Aerospace Science and Technology 24, no. 1 (January 2013): 56–65. http://dx.doi.org/10.1016/j.ast.2012.03.002.

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Goerttler, Andreas, Johannes N. Braukmann, C. Christian Wolf, Anthony D. Gardner, and Markus Raffel. "Blade Tip-Vortices of a Four-Bladed Rotor with Axial Inflow." Journal of the American Helicopter Society 65, no. 4 (October 1, 2020): 1–13. http://dx.doi.org/10.4050/jahs.65.042002.

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The vortex system of four rotating and pitching DSA-9A blades was examined numerically and experimentally. Numerical computations were performed using German Aerospace Center (DLR)'s finite-volume solver TAU and were validated against experimental data gathered using particle image velocimetry carried out at the rotor test facility (RTG) in Göttingen. Algorithms deriving the vortex position, swirl velocity, circulation, and core radius were implemented. Hover-like conditions with a fixed blade pitch were analyzed giving further physical insights of the static vortex system. These results are used to understand the vortex development for the unsteady pitching conditions, which can be described as a superpositioning of static vortex states. The use of a zonal detached-eddy simulations approach improved physical modeling of the vortex development by resolving finer scales than URANS. Trimmed cases agree well with differences less than 0.5% in the circulation and swirl velocity.

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Gomez, Ignacio, Miguel Chavez, Gustavo Alonso, and Eusebio Valero. "Numerical Investigation of Galloping Instabilities in Z-Shaped Profiles." Scientific World Journal 2014 (2014): 1–14. http://dx.doi.org/10.1155/2014/363274.

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Aeroelastic effects are relatively common in the design of modern civil constructions such as office blocks, airport terminal buildings, and factories. Typical flexible structures exposed to the action of wind are shading devices, normally slats or louvers. A typical cross-section for such elements is a Z-shaped profile, made out of a central web and two-side wings. Galloping instabilities are often determined in practice using the Glauert-Den Hartog criterion. This criterion relies on accurate predictions of the dependence of the aerodynamic force coefficients with the angle of attack. The results of a parametric analysis based on a numerical analysis and performed on different Z-shaped louvers to determine translational galloping instability regions are presented in this paper. These numerical analysis results have been validated with a parametric analysis of Z-shaped profiles based on static wind tunnel tests. In order to perform this validation, the DLR TAU Code, which is a standard code within the European aeronautical industry, has been used. This study highlights the focus on the numerical prediction of the effect of galloping, which is shown in a visible way, through stability maps. Comparisons between numerical and experimental data are presented with respect to various meshes and turbulence models.

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Kirz, Jochen. "DLR TAU Near-Field Simulations for the Third AIAA Sonic Boom Prediction Workshop." Journal of Aircraft, July 14, 2021, 1–13. http://dx.doi.org/10.2514/1.c036397.

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Xing, Wenmin, Wenyan Gao, Xiaoling Lv, Xiaogang Xu, Zhongshan Zhang, Jing Yan, Genxiang Mao, and Zhibin Bu. "The Diagnostic Value of Exosome-Derived Biomarkers in Alzheimer's Disease and Mild Cognitive Impairment: A Meta-Analysis." Frontiers in Aging Neuroscience 13 (March 1, 2021). http://dx.doi.org/10.3389/fnagi.2021.637218.

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Background: Alzheimer's disease (AD) diagnoses once depended on neuropathologic examination. Now, many widely used, validated biomarkers benefits for monitoring of AD neuropathologic changes. Exosome-derived biomarker studies have reported them to be significantly related to AD's early occurrence and development, although the findings are inconclusive. The aim of this meta-analysis was to identify exosome-derived biomarkers for the diagnosis of AD and mild cognitive impairment (MCI).Methods: PubMed, PubMed Central, Web of Science, Embase, Google Scholar, Cochrane Library, the Chinese National Knowledge Infrastructure (CNKI), and the Chinese Biomedical Literature Database (CBM) were searched for studies assessing the diagnostic value of biomarkers, including data describing the pooled sensitivity (SEN), specificity (SPE), positive diagnostic likelihood ratio (DLR+), negative diagnostic likelihood ratio (DLR–), diagnostic odds ratio (DOR), and area under the curve (AUC). The quality of the included studies was assessed using RevMan 5.3 software. Publication bias was analyzed.Results: In total, 19 eligible studies, including 3,742 patients, were selected for this meta-analysis. The SEN, SPE, DLR+, DLR–, DOR, and AUC (95% confidence intervals) of exosome-derived biomarkers in the diagnosis of AD or MCI were 0.83 (0.76–0.87), 0.82 (0.77–0.86), 4.53 (3.46–5.93), 0.21 (0.15–0.29), 17.27 (11.41–26.14), and 0.89 (0.86–0.92), respectively. Sub-group analyses revealed that studies based on serum or microRNA (miRNA) analysis, and those of Caucasian populations, AD patients, patient sample size >50, neuron-derived exosomes (NDE) from plasma and p-tau had higher sensitivity, specificity, and AUC values.Conclusion: Exosome-derived biomarkers have shown potential diagnostic value in AD and MCI, although further research is required for confirmation.

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Dissertations / Theses on the topic "DLR-TAU"

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Mazzacchi, Francesco. "Evaluation of the TAU CFD solver for steady and unsteady turbulent flow analysis of a supercritical wing." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2017. http://amslaurea.unibo.it/13370/.

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The present work is part of a long-term project aimed at the validation and development of the code in DLR-TAU CFD solver in order to predict the steady and unsteady flow fields, forced and unforced motion and aeroelastic response. The strategy to validate these methods consists of the identification and quantification of errors in the computational models and the evaluation of the calculation results with the experimental data. The experimental data were obtained from NASA Langley Transonic Dynamics Tunnel. The aim is to assess the state-of-the-art Computational Aeroelasticity methods for the prediction of dynamic and static aeroelastic phenomena. All of this is based on the first and second AIAA Aeroelastic Prediction Workshops, where the (BSCW) Benchmark Supercritical Wing has been chosen as a reference point for these workshops. The BSCW has a simple geometrical structure, with a rectangular planform and it is considered to be a rigid structure. Three different Test Cases have been determined with different and pre-fixed angles of attack. The simulations were carried out in the transonic range with Mach numbers between 0.70 $\div$ 0.85 where different flow phenomena may occur and cause serious problems, such as aeroelastic flutter, buffet, and limit cycle oscillations. The author used the DLR-TAU code implemented by Reynolds-averaged Navier-Stokes (RANS) equations. Several computational setups are implemented and two different types of turbulence models: (SA) Spalart-Allmaras and the (k-$\omega$ SST) Shear Stress Transport. At the end of this work two different approaches have been compared; the RANS simulations from DLR-Tau and the hybrid from SU2. The latter was carried out by another participant. Both approaches can resolve the largest turbulent structures, but only the hybrid approach can provide significant solutions.

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Book chapters on the topic "DLR-TAU"

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Weinman, K. A. "Vortical Modeling in the DLR TAU Code." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 439–46. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-35680-3_52.

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Schwamborn, D., T. Gerhold, and V. Hannemann. "On the Validation of the DLR-TAU Code." In Notes on Numerical Fluid Mechanics (NNFM), 426–33. Wiesbaden: Vieweg+Teubner Verlag, 1999. http://dx.doi.org/10.1007/978-3-663-10901-3_55.

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Krimmelbein, Normann. "Industrialization of the Automatic Transition Prediction in the DLR TAU Code." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 89–98. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38877-4_7.

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Schwöppe, Axel, and Boris Diskin. "Accuracy of the Cell-Centered Grid Metric in the DLR TAU-Code." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 429–37. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-35680-3_51.

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Lüdeke, H., and A. Filimon. "Time Accurate Simulation of Turbulent Nozzle Flow by the DLR TAU-Code." In New Results in Numerical and Experimental Fluid Mechanics V, 305–12. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_38.

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Krumbein, A., N. Krimmelbein, and G. Schrauf. "Automatic Transition Prediction for Three-Dimensional Aircraft Configurations Using the DLR TAU Code." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 101–8. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14243-7_13.

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Burggraf, U., M. Kuntz, and B. Schöning. "Implementation of the Chimera Method in the Unstructured DLR Finite Volume Code Tau." In Notes on Numerical Fluid Mechanics (NNFM), 93–100. Wiesbaden: Vieweg+Teubner Verlag, 1999. http://dx.doi.org/10.1007/978-3-663-10901-3_13.

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Spiering, Frank. "Development of a Fully Automatic Chimera Hole Cutting Procedure in the DLR TAU Code." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 585–95. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27279-5_51.

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Widhalm, M., and C. C. Rossow. "Improvement of upwind schemes with the Least Square method in the DLR TAU Code." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 398–406. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39604-8_50.

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Stuermer, Arne. "Unsteady Euler and Navier-Stokes Simulations of Propellers with the Unstructured DLR TAU-Code." In New Results in Numerical and Experimental Fluid Mechanics V, 144–51. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_18.

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Conference papers on the topic "DLR-TAU"

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Gauer, Markus, Volker Hannemann, and Klaus Hannemann. "Implementation of the VOF Method in the DLR TAU Code." In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-4863.

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Kroll, Norbert, Stefan Langer, and Axel Schwöppe. "The DLR Flow Solver TAU - Status and Recent Algorithmic Developments." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-0080.

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Mack, Andreas, and Volker Hannemann. "Validation of the Unstructured DLR-TAU-Code for Hypersonic Flows." In 32nd AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3111.

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Gerhold, T., M. Galle, O. Friedrich, J. Evans, T. Gerhold, M. Galle, O. Friedrich, and J. Evans. "Calculation of complex three-dimensional configurations employing the DLR-tau-code." In 35th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-167.

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Kirz, Jochen, and Ralf Rudnik. "DLR TAU Simulations for the Second AIAA Sonic Boom Prediction Workshop." In 35th AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3253.

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Oblapenko, G. P., E. V. Kustova, K. Hannemann, and V. Hannemann. "Assessment of recent thermo-chemical relaxation models using the DLR-TAU code." In 31ST INTERNATIONAL SYMPOSIUM ON RAREFIED GAS DYNAMICS: RGD31. AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5119640.

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Crippa, Simone, and Normann Krimmelbein. "Transitional Flow Computations of the NASA Trapezoidal Wing with the DLR TAU Code." In 30th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2845.

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Stuermer, Arne W. "Assessing Turbofan Modeling Approaches in the DLR TAU-Code for Aircraft Aerodynamics Investigations." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-0277.

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Kirz, Jochen. "DLR TAU Simulations for the Third AIAA Sonic Boom Prediction Workshop Near-Field Cases." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-0472.

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Andres, Esther, Markus Widhalm, and A. Caloto. "Achieving High Speed CFD Simulations: Optimization, Parallelization, and FPGA Acceleration for the Unstructured DLR TAU Code." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-759.

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