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29 results for “ENODISE”
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: Experimental dataset of configuration C VKI
<p>This database includes experimental aerodynamic and acoustic data for configuration C as defined in the H2020 ENODISE project (https://www.vki.ac.be/index.php/about-enodise). Single and contra-rotating propeller loads and far-field noise were measured in anechoic facility ALCOVES at von Karman Institute for Fluid Dynamics, Belgium. The description of the experimental tests is reported in the associated technical file.</p>
H2020 Enodise: Experimental dataset of configuration B with mitigation TUD
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H2020 Enodise: Analytical dataset configuration B2 ECL
<p>This dataset considers analytical data for configuration B2 as defined in the H2020 ENODISE project (https://www.vki.ac.be/index.php/about-enodise). The results were calculated using the half-plane Green's function for the convected Helmholtz equation for predicting the sound scattering by trailing edges in the presence of a uniform flow. For mimicking the Distributed Electric Propulsion (DEP) configuration model which includes a wing and two side-by-side propellers measured during the wind tunnel tests, the formalism of source-modes is introduced, from which the sound field could be expressed uniformly in the whole space. The wing was approximated by a thin plate with zero-thickness. The aerodynamic performance of the propeller was calculated by using a BEMT method.</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>
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>
H2020 ENODISE: VKI Experimental dataset of configuration C with mitigation
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