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17 results for “aeroacoustics”
Aeroacoustic investigations of streamwise vortex generators for boundary layer separation control.
<p>This project contains the data obtained as a result of the Preludium Grant no 2022/45/N/ST8/01425 of the Polish National Science Centre fundings. Within the "Aeroacoustic investigations of streamwise vortex generators for boundary layer separation control" project, two main research tasks were defined:<br> 1. Implementation of porous FW-H analogy into the developed aeroacoustic code.<br> 2. Validation of the porous FW-H analogy implementation against analytical solutions for elementary sources.</p> <p>The resutls from these tasks are uploaded here. The details of the data are included in the EOP_medata_2.docx document uploaded. </p>
H2020 ENODISE: ONERA Numerical Aeroacoustic Database Configuration A2-Ducted
<p>This database contains the numerical results obtained by ONERA on the configuration A2-ducted of the H2020 ENODISE project. In this configuration, a ducted propeller is placed above an S-plate to ingest an adverse pressure gradient boundary layer in a partially buried configuration. The present results can be compared to the measurements carried out by the University of Bristol.</p> <p>All following parameters are kept constant in the present simulations:</p> <ul> <li>Free-stream velocity <em>u_inf</em> = 32 m/s,</li> <li>Propeller tip clearance <em>d/D</em> = 0.002,</li> <li>Propeller position inside the duct <em>x/D</em> = -0.0627.</li> </ul> <p>Five simulations have been realized by varying the installation (with or without the S-plate) and the propeller rotation speed:</p> <ul> <li>Isolated propeller (without the S-plate), <em>N</em> = 6000 rpm, 8000 rpm, 11000 rpm,</li> <li>Installed propeller (with the S-plate), <em>N</em> = 6000 rpm, 8000 rpm.</li> </ul> <p>The predictions were obtained using the ProLB solver which is based on the Lattice Boltzmann method (<a href="http://www.prolb-cfd.com/">http://www.prolb-cfd.com/</a>). Aerodynamic and acoustic results are provided for each simulation. One-dimensional results are saved into ASCII column files (<em>.dat</em> extension) while geometry and raw flow extractions are saved into HDF5 CGNS files (<em>.cgns</em> extension). <em>README.txt</em> files are included for detailed description of the data.</p> <p> </p>
H2020 ENODISE: SISW Numerical Aeroacoustic Database Configuration B2
<p>This database contains the aeroacoustic numerical results generated by Siemens Industry Software (SISW) for the B2 configuration investigated in the framework of the European project ENODISE. In this configuration, a six-blade propeller mounted on a support is studied for two operating points with and without flow. The operating points correspond to conditions 65 and 66 of the experimental campaign carried out at Ecole Centrale of Lyon (see H2020 Enodise: Experimental dataset configuration B2 ECL, https://zenodo.org/record/7925336).</p> <p>The two investigated operating points are:</p> <ul> <li>Uinf = 0 studied numerically using detached-eddy simulation combined with finite-element method for acoustics</li> <li>Uinf = 22 m/s studied numerically using large-eddy simulation combined with finite-element method for acoustics</li> </ul> <p>The SISW aeroacoustic results have been obtained using CFD software Simcenter STAR-CCM+ coupled with acoustic software Simcenter 3D Acoustics. The hydrodynamic and acoustic interactions between the propeller and its support are taken into account in the numerical simulations.</p> <p>More information about the numerical setup and results can be found in the documentation included in the database.</p> <p>The data are saved in dat files.</p>
H2020 ENODISE: ONERA Numerical Aeroacoustic Database of Configuration C
<p>This database contains the acoustic prediction results realized by ONERA of the configuration C investigated in the framework of the European project ENODISE. In this configuration, contra-rotating propellers are investigated in static condition with and without shroud. The results presented here can be compared to the measurements carried out by von Karman Institute for Fluid Dynamics in anechoic facility ALCOVES (https://zenodo.org/record/7966211).</p> <p>The investigated operating point as calculated in the prediction is:</p> <ul> <li>Shrouded, RPM=6000, d=3cm.</li> <li>Unshrouded, RPM=6000, d=3cm.</li> </ul> <p>Predictions were obtained using the ProLB code based on a Lattice Botlzmann Method.</p> <p>Description of the database is proposed in the document <em>Database_ENODISE_ONERA_ConfigurationC.pdf.</em></p>
H2020 ENODISE: NLR Numerical aeroacoustic database configuration B3-flap
<p>This dataset considers numerical aerodynamic and aeroacoustic data for an over-the-wing mounted propeller, denoted configuration B3-flap as defined in the H2020 ENODISE project (https://www.vki.ac.be/index.php/about-enodise).</p> <p>The dataset consists of</p> <p>- Aerodynamic data: propeller thrust and torque</p> <p>- Acoustic data: pressure Fourier modes at 1, 2, and 3 BPF</p> <p>both for the isolated propeller and the over-the-wing mounted propeller.</p> <p>An overview of the performed numerical simulation and a description of the dataset is given in the included PDF file (ENODISE_NLR_B3_flap_URANS.pdf). This file also includes the aerodynamic data.</p> <p>Experiments have also been performed by NLR for this configuration. See https://zenodo.org/record/8283630 for details and the experimental dataset.</p>
H2020 ENODISE: DLR Analytical Aeroacoustic Database BLI Configuration A1 and A2
<p>This database contains the acoustic prediction results of DLR for a single operating point of the A1 and A2 configurations investigated in the framework of the European project ENODISE. In these configurations, a single two-bladed propeller is immersed in a boundary layer. The present results can be compared to the measurements carried out by the University of Bristol and the University of Twente for different boundary layer characteristics. The experimental results are saved elsewhere on the ZENODO repository.</p> <p>The investigated operating point as calculated in the prediction is:</p> <ul> <li>Uinf = 33 m/s, 6500 rpm, advance ratio J=1.</li> </ul> <p>The experimental measurements were conducted at a slightly lower freestream velocity.</p> <p>The DLR prediction results were obtained using the analytical approach implemented in the DLR in-house program PropNoise coupled to the blade element momentum theory. The calculations were informed by the hot-wire measurements carried out in the boundary-layer as the propeller was removed.</p> <p>Refer to the two references cited below to obtain more information about the theory that was applied to obtain the results: </p> <ol> <li> S. Guérin, T. Lade, L. Castelucci, I. Zaman, Tonal noise emission by a low-Mach low-Reynolds number propeller ingesting a boundary layer, 29th International Congress on Sound and Vibration, 10-13 July 2023, Prague (CZ).</li> <li> S. Guérin, T. Lade, L. Castelucci, I. Zaman, Broadban noise emission by a low-Mach low-Reynolds number propeller ingesting a boundary layer, Inter-Noise 2023, 20-23 August 2023, Chiba (Great Tokyo), Japan.</li> </ol> <p>The results for tonal and broadband noise are saved separately. The DLR results are saved into an h5 file, which can be read with e.g. python.</p> <p>Further details can be found in the file <em>DLR_documentation_A1_A2.pptx</em></p>
H2020 ENODISE: DLR Analytical Aeroacoustic Database Configuration B1
<p>This database contains the acoustic prediction results of DLR for a single operating point of the B1 configuration investigated in the framework of the European project ENODISE. In this configuration, three identical propellers with 6 blades are mounted at leading-edge of a wing (puller configuration). The results presented here can be compared to the measurements carried out by the Technical University of Delft, when these are available. The experimental results should be also saved on the ZENODO repository (use the key word ENODISE).</p> <p>The investigated operating point as calculated in the prediction is:</p> <ul> <li>Uinf = 30 m/s, advance ratio J=0.8.</li> </ul> <p>The DLR prediction results were obtained using the analytical approach implemented in the DLR in-house program PropNoise coupled to the blade element momentum theory.</p> <p>The interaction with the wing is accounted for in a simplistic way as explained in the detailed documentation <em>B_documentation.pptx.</em></p> <p>Only, the results for tonal noise are available in this database. Three cases can be investigated separately: a single isolated propeller, 3 distributed propellers, three distributed propellers interacting with the wing.</p> <p> </p> <p>The DLR results are saved in h5 files, which can be read with e.g. Python.</p>
H2020 ENODISE: VKI Numerical Aeroacoustic Database of Configuration B1
<p>This database represents the resultant data from a hybrid methodology consisting of aerodynamic simulations using uRANS and acoustic propagation simulations using FEM. The simulation of both the aerodynamic installation effects and the acoustic installation effects is available. The data from the aerodynamic simulations is given in the<em> .cgns </em>format and are in the <em>Aerodynamic_Results</em> folder. The resulting acoustic directivities from these sources using the FEM-Source Mode method are stored in the <em>Acoustic_Results</em> folder as <em>.csv </em>files. Both folders have a README file available with more details.</p>
H2020 ENODISE: VKI and SISW Numerical Aeroacoustic Database of Configuration C
<p>The hybrid aeroacoustic methodology prediction findings produced by VKI and SISW for configuration C within the scope of the European project ENODISE are contained in this database. In this setup, contra-rotating propellers with and without a shroud are investigated. Simulations of single rotors with and without the shroud are also included. The measurements made at the anechoic facility ALCOVES at VKI (https://zenodo.org/record/7966211) and further simulations made by ONERA (https://zenodo.org/record/8191815) can be compared to the findings provided here . </p> <p>A description of the numerical set up and database file structure are included in the PDF: <em>VKI-SISW_Simulation_Methodology_and_File_Organization_Config_C.pdf</em></p> <p><br> </p>
VORTEX 01: Analytic solution of the flow, aeroacoustic source and acoustic field from a co-rotating vortex pair
<div>This aeroacoustic reference example (often referred in literature as "Co-rotating vortex pair") provides the analytic solution of the flow, aeroacoustic source and acoustic field. Details on the example and derivation can be found in the article "Analysis of the co-rotating vortex pair as a test case for computational aeroacoustics" on which the analytic functions are based on can be found here: <a title="Persistent link using digital object identifier" href="https://doi.org/10.1016/j.jsv.2024.118496" target="_blank" rel="noopener">10.1016/j.jsv.2024.118496</a>. The following Matlab functions can be used for computing the aero-acoustic radiation of a co-rotating vortex pair:</div> <div> </div> <div><strong>Main script:</strong></div> <div>compute_pfar - Computes the radiated acoustic field. Use the "method" variable to change the aeroacoustic model</div> <div> </div> <div><strong>Computing the source terms:</strong></div> <div>vpair_pic - Incompressible pressure field p_ic and Dp_ic / Dt at a given time instance</div> <div>vpair_u - Velocity field u, and its first and second spatial derivatives at a given time instance</div> <div> </div> <div>plot_source_terms - Create a plot of the source terms of both Lighthill and PCWE</div> <div>plot_quadrupole_field - Plots the analytical quadrupole field solution</div> <div> </div> <div><strong>Utility functions used by the main script:</strong></div> <div>gaussquad - Gauss-Legendre quadrature in 1D (original version from Mathworks FTP)</div> <div>subdiv_graded - Graded subdivision of one or more sections in 1D</div> <div>vpair_quadrature - Quadrature base points and weights for numerical convolution</div> <div> </div> <div><strong>Resource:</strong></div> <div>colormap.png - Blue -> Gray -> Red color scale</div> <div> </div> <div>All functions and scripts, except gaussquad.m were created by the authors:</div> <div>P. Rucz, M. Á. Ulveczki, J. Heinz, S. Schoder</div>
A comparison between SBP-SAT and DG operators for computational aeroacoustics on non-conforming meshes
<p>Contains:</p> <ul> <li>classic SBP operators of global order three, four and five</li> <li>classic DRP SBP operators of global order three, four and five</li> <li>DDRP SBP operator of order four using 32 nodes</li> <li>Projection operators for h- and p-refinement</li> </ul>
H2020 ENODISE: RWTH Numerical Aeroacoustic Database Configuration B1
<p>This RWTH dataset contains numerical data for aerodynamics and acoustics of configuration B1, which was defined in the H2020 ENODISE project (<a href="https://www.vki.ac.be/index.php/about-enodise">https://www.vki.ac.be/index.php/about-enodise</a>). In this configuration, three 6-bladed XPROP-S propellers are installed side-by-side on the leading edge of a wing with an airfoil shape of NLF-Mod22(B).</p> <p>The investigated operating point is:</p> <ul> <li>The incoming flow velocity <em>U∞</em> = 30 m/s, the wing angle of attack <em>AoA </em>= 2 deg, the propeller advance ratio <em>J</em> = 0.8, and the relative blade phase angle between propellers <em>∆Φ </em>= 0.</li> </ul> <p>Wall-resolved Large eddy simulations (LES) of the configuration are performed based on the multiphysics flow solver m-AIA of RWTH. The far-field noise is predicted by the Ffowcs-Williams and Hawkings (FW-H) method. The data set contains the time-averaged aerodynamic results predicted by the LES simulation and the aeroacoustic results calculated by the FW-H method. It should be noted that the aeroacoustic data is only a preliminary result and it will be updated soon.</p> <p>More details of the simulation and measurement setups are explained in the attached document ENODISE_B1_RWTH.pptx.</p>
H2020 ENODISE: Numerical Aeroacoustic Database Configuration A1 : GPUP
<p>This dataset contains the numerical prediction for A1 configuration as defined in the H2020 ENODISE project (<a href="https://www.vki.ac.be/index.php/about-enodise">https://www.vki.ac.be/index.php/about-enodise</a>). In this configuration, a single two-bladed propeller is immersed in a boundary layer. The present results can be compared to the measurements carried out by the University of Bristol.</p> <p> The investigated operating point as calculated in the prediction is:</p> <ul> <li>Uinf = 33 m/s, 6500 rpm, advance ratio J=1</li> </ul> <p>The results were calculated using the LES-CABARET method on GPUs. The results presented are preliminary result on coarse grid with the comparison with the experiment for hot-wire and overhead acoustic data at 60-, 90- and 120-degree observer angles.</p>
H2020 ENODISE: Numerical Aeroacoustic Database Configuration A2 : GPUP
<p>This dataset contains the numerical prediction for A2 configuration as defined in the H2020 ENODISE project (<a href="https://www.vki.ac.be/index.php/about-enodise">https://www.vki.ac.be/index.php/about-enodise</a>). In this configuration, a single two-bladed propeller is immersed in a boundary layer. The present results can be compared to the measurements carried out by the University of Bristol.</p> <p> The investigated operating point as calculated in the prediction is:</p> <ul> <li>Uinf = 27 m/s, RPM = 6500</li> </ul> <p>The results were calculated using the LES-CABARET method on GPUs. The results presented are preliminary result on coarse grid with the comparison with the experiment for hot-wire and overhead and side-array acoustic data at 60-120-degree observer angles. In the initial preliminary results, the propeller is located at 1000mm from the inlet. More results will follow. </p>
H2020 ENODISE: UR3 Aeroacoustic processing Configuration A1
<p>This database encompasses post-processing results derived from experiments conducted at the University of Bristol, specifically focusing on configuration A1. In this research, two distinct boundary layer thicknesses were taken into account, with an analysis comparing the performance of 3-bladed and 5-bladed propellers. The freestream velocity maintained a constant value of 20 m/s, and the chosen advance ratio (J) spanned the range of [0.56, 0.98].</p> <p>The dataset includes information such as the Overall Sound Pressure Level, Haystacking Maps, and Spectra Scaling. These metrics are provided for four different scenarios, each involving variations in the number of blades and boundary layer thickness.</p>
Propeller aerodynamics and aeroacoustics [section 1.6]
<p>Aerodynamic and aeroacoustic prediction methods for rotor performance</p>
H2020 ENODISE: ONERA Numerical Aeroacoustic Database Configuration B1
<p>The ONERA numerical database on configuration B1 deals with the scattering effects of 3 side-by-side puller propellers installed upstream a wing profile in a flow, using an in-house 3-steps-chaining-method. The aim of this work has been to evaluate the ability of the method to predict the scattering effects on the sound pressure level and its directivity.</p> <p><br> The two operating points that have been studied are:<br> • U∞ = 30 m/s, J = 0.8, AoA = 2°, with a blade phase-angle Φ=0° between the middle and the side propellers<br> • U∞ = 30 m/s, J = 0.8, AoA = 2°, with a blade phase-angle Φ=10° between the middle and the side propellers</p> <p>The present configuration follows the one described in TUD experimental contribution for configuration B1.</p> <p>A synthetized description of the numerical method including some important details and results will be included in the file ONERA_B1_configuration.pptx.</p> <p>The ONERA database contains numerical results about aerodynamic performances (thrust, torque and efficiency). It also includes pressure and sound pressure levels on the arcs microphones positions of TUD experimental configuration.<br> Data are stored in .dat and .plt format files.</p>
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