About

This database contains experimental data of wind tunnel measurements for propellers used on small UAVs and model aircraft provided by the UIUC Department of Aerospace and Engineering.

It was downloaded and organized by me in the presented format to facilitate machine learning applications. The Database is compose of two types of dataset, the experiment, which contains information regarding experiments on the propellers and the geometry, which contains information regarding propellers' geometry. There are 3 different versions, all related to different works produced by the academic body of the university.

Experiment Data Set Features:

PropName: Propeller's Name. BladeName: Blade's Name. Family: Propeller's Brand. B: Number of Blades. D: Propeller's Diameter. P: Propeller's Pitch. J: Advanced Ratio Input. N: RPM Rotation Input. CT: Thrust Coefficient Output. CP: Power Coefficient Output. eta: Efficiency Output.

Blade Geometry Data Set Features:

PropName: Propeller's Name. BladeName: Blade's Name. Family: Propeller's Brand. D: Propeller's Diameter. P: Propeller's Pitch. r/R: Adimensional Radius. c/R: Adimensional Chord. beta: Angle Relative to Rotation.

Data Source

J.B. Brandt, R.W. Deters, G.K. Ananda, O.D. Dantsker, and M.S. Selig (insert date downloaded), UIUC Propeller Database, Vols 1-3, University of Illinois at Urbana-Champaign, retrieved from https://m-selig.ae.illinois.edu/props/propDB.html.

Works

Rosa, Heitor Nunes Performance prediction of small propellers with XGBoost: effects of the solidity imputation process by regression methods. Universidade Estadual Paulista (Unesp), 2022. Avaliable in: http://hdl.handle.net/11449/217119.

Dos Santos, Miguel Cabeleira. Analytical Model for the Performance Curves of a Family of Propellers Based on Wind Tunnel Tests. Diss. Universidade da Beira Interior (Portugal), 2018. Avaliable in: http://hdl.handle.net/10400.6/8437

516 Global export shipment records of Aircraft Propeller with prices, volume & current Buyer's suppliers relationships based on actual Global export trade database.

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).

The investigated operating point as calculated in the prediction is:

Uinf = 30 m/s, advance ratio J=0.8.

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 interaction with the wing is accounted for in a simplistic way as explained in the detailed documentation B_documentation.pptx.

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.

The DLR results are saved in h5 files, which can be read with e.g. Python.

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). The two investigated operating points are: Uinf = 0 studied numerically using detached-eddy simulation combined with finite-element method for acoustics Uinf = 22 m/s studied numerically using large-eddy simulation combined with finite-element method for acoustics 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. More information about the numerical setup and results can be found in the documentation included in the database. The data are saved in dat files.

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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. All following parameters are kept constant in the present simulations: Free-stream velocity u_inf = 32 m/s, Propeller tip clearance d/D = 0.002, Propeller position inside the duct x/D = -0.0627. Five simulations have been realized by varying the installation (with or without the S-plate) and the propeller rotation speed: Isolated propeller (without the S-plate), N = 6000 rpm, 8000 rpm, 11000 rpm, Installed propeller (with the S-plate), N = 6000 rpm, 8000 rpm. The predictions were obtained using the ProLB solver which is based on the Lattice Boltzmann method (http://www.prolb-cfd.com/). Aerodynamic and acoustic results are provided for each simulation. One-dimensional results are saved into ASCII column files (.dat extension) while geometry and raw flow extractions are saved into HDF5 CGNS files (.cgns extension). README.txt files are included for detailed description of the data.

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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). The dataset consists of - Aerodynamic data: propeller thrust and torque - Acoustic data: pressure Fourier modes at 1, 2, and 3 BPF both for the isolated propeller and the over-the-wing mounted propeller. 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. Experiments have also been performed by NLR for this configuration. See https://zenodo.org/record/8283630 for details and the experimental dataset.

This database contains the numerical results obtained by ONERA on the configuration A1, using ZDES mode 2 and ZDES mode 3 methods. The ZDES mode 3 approach offers an explicit resolution of the turbulent scales present in the outer region of the flat plate boundary layer and their interaction with the propeller.

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This dataset considers experimental aerodynamic and aeroacoustic data for configuration B3 as defined in the H2020 Enodise project (https://www.vki.ac.be/index.php/about-enodise):

Configuration B3 has been split into two subconfigurations (B3-VTOL and B3-FLAP). The available data for two subconfigurations are given below.

B3-VTOL (side-by-side rotor setup):

- Time-resolved 2D2C Velocity fields

- 4D-PTV tracks

B3-FLAP (over-the-wing distributed propulsion):

- Propeller thrust and torque (for isolated propeller, over-the-wing propeller, over-the-wing distributed propellers)

- Acoustic microphone data (for isolated propeller, over-the-wing propeller, over-the-wing distributed propellers)

- Wing static pressures (for over-the-wing propeller, over-the-wing distributed propellers)

- Time-averaged 2D3C Velocity fields (for over-the-wing propeller)

- Time-averaged 2D2C Velocity fields (for over-the-wing distributed propellers)

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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.

The investigated operating point as calculated in the prediction is:

Uinf = 33 m/s, 6500 rpm, advance ratio J=1.

The experimental measurements were conducted at a slightly lower freestream velocity.

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.

Refer to the two references cited below to obtain more information about the theory that was applied to obtain the results:

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).

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.

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.

Further details can be found in the file DLR_documentation_A1_A2.pptx

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