This dataset contains a curated set of 19,164 airfoil shapes from various applications and the data-driven design space of separable shape tensors (PGA space), which can be used as a parameter space for machine-learning applications focused on airfoil shapes. We constructed the airfoil dataset in two main stages. First, we identified 13 baseline airfoils from the NREL 5MW and IEA 15MW reference wind turbines. We reparameterized these shapes using least-squares fits of 8-order CST parametrizations, which involve 18 coefficients. By uniformly perturbing all 18 CST coefficients by +/-20% around each baseline airfoil, we generated 1,000 unique airfoils. Each airfoil was sampled with 1,001 shape landmarks whose x-coordinates followed a cosine distribution along the chord. This process resulted in a total of 13,000 airfoil shapes, each with 1,001 landmarks. In the second phase, we gathered additional airfoils from the extensive BigFoil database, which consolidates data from sources such as the University of Illinois Urbana-Champaign (UIUC) airfoil database, the JavaFoil database, the NACA-TR-824 database, and others. We undertook a thorough pre-processing step to filter out shapes with sparse, noisy, or incomplete data. We also removed airfoils with sharp leading edge and those exceeding our threshold for trailing edge thickness. Additionally, we thinned out the collection of NACA airfoils-- parametric sweeps of NACA airfoils with increasing thickness and camber present in BigFoil database-- by selecting every fourth step in the parameter sweeps. Finally, we regularized the airfoils by reparametrizing them with an 8-order CST parametrization (with 1,001 shape landmarks with x coordinated following cosine distribution along the chord) and removing airfoils with high reconstruction errors. This data pre-processing resulted in a set of 6,164 airfoils. In total, our curated airfoil dataset comprises 19,164 airfoils, each with 1,001 landmarks, and is stored in the curated_airfoils.npz file. Using this curated airfoil dataset, we utilized the separable shape tensors framework to develop a data-driven parameterization of airfoils based on principal geodesic analysis (PGA) of separable shape tensors. This PGA space is provided in PGAspace.npz file.

This dataset contains aerodynamic quantities - including flow field values (momentum, energy, and vorticity) and summary values (coefficients of lift, drag, and momentum) - for 1,830 airfoil shapes computed using the HAM2D CFD (computational fluid dynamics) model. The airfoil shapes were designed using the separable shape tensor parameterization that encodes two-dimensional shapes as elements of the Grassmann manifold. This data-driven approach learns two independent spaces of parameter from a collection of sample airfoils. The first captures large-scale, linear perturbations, and the second defines small-scale, higher-order perturbations. For this dataset, we used the G2Aero database of over 19,000 airfoil shapes to learn a parameter space that captured a wide array of shape characteristics. We sampled airfoil designs over both parameter spaces to explore the full range of possible shape variations. The aerodynamic quantities for the generated airfoil were obtained using the HAM2D code, which is a finite-volume Reynolds-averaged Navier-Stokes (RANS) flow solver. We employ a fifth-order WENO scheme for spatial reconstruction with Roe's flux difference scheme for inviscid flux and second-order central differencing for viscous flux. A preconditioned GMRES method is applied for implicit integration. The Spalart-Allmaras 1-eq turbulence model is used for the turbulence closure, and the Medida-Baeder 2-eq transition model is applied to account for the effects of laminar turbulent transition. The airfoil grid is generated with a total of 400 points on the airfoil surface, the initial wall-normal spacing of y+ = 1, and an outer boundary located at 300 chord lengths away from the wall. The CFD simulations are performed at a freestream Mach number of 0.1, for or three different Reynolds' numbers (3M, 6M, and 9M), and for 25 angles of attack from -4 deg. to 20 deg. with 1 degree increments. Across all these various parameters, this dataset includes the results from over 250,000 CFD simulations. The simulations were performed using the Bridges-2 system at the Pittsburgh Supercomputing Center in February 2023 as part of the INTEGRATE project funded by the Advanced Research Projects Agency - Energy, in the U.S. Department of Energy. The data was collected, reformatted, and preprocessed for this OEDI submission in July 2023 under the Foundational AI for Wind Energy project funded by the U.S. Department of Energy Wind Energy Technologies Office. This dataset is intended to serve as a benchmark against which new artificial intelligence (AI) or machine learning (ML) tools may be tested. Baseline AI/ML methods for analyzing this dataset have been implemented, and a link to their repository containing those models has been provided. The .h5 data file structure can be found in the GitHub Repository resource under explore_airfoil_2k_data.ipynb.

This dataset is designed to test Machine-Learning techniques on Computational Fluid Dynamics (CFD) data.

It contains two-dimensional RANS simulations of the turbulent flow around NACA 4-digits airfoils, at fixed angle of attack (10 degrees) and at a fixed Reynolds number (3x10^6). The whole NACA family is spawned.

The present dataset contains 425 geometries, 2600 further geometries are published in accompanying repository (10.5281/zenodo.4106752).

For further information refer to: Schillaci, A., Quadrio, M., Pipolo, C., Restelli, M., Boracchi, G. "Inferring Functional Properties from Fluid Dynamics Features" 2020 25th International Conference on Pattern Recognition (ICPR) Milan, Italy, Jan 10-15, 2021

Rectangular Supercritical Wing (Ricketts) - design and measured locations are provided in an Excel file RSW_airfoil_coordinates_ricketts.xls . One sheet is with Non dimensional coordinates (RSW-nd) to be able to compare with other supercritical airfoils. The other sheet (RectSupercriticalWing) has the data which should be used to generate the grids. Benchmark Supercritical Wing are available in PDF file of tables. The data was OCR'd. Matlab code was written to read data line by line to be able to extract the data. The "*" flag associated with points that have deviation greater the specified value were replaced with blank space. Bad lines were omitted - lines that have non-numerical digits. Comparison of Rectangular Supercritical Wing (Ricketts), Benchmark Supercritical Wing, MBB_A3 2D Airfoil tested at DLR - comparison of theoretical and actual.

This dataset contains data from a three-dimensional large eddy simulation of Mach 0.3 flow over a NACA 0012 airfoil at Reynolds number 23,000, which features a transitional boundary layer, separation over a recirculation bubble, and a turbulent wake. The dataset contains 16,000 time-resolved snapshots of the mid-span and spanwise-averaged velocity fields. All data are stored within hdf5 files, and a Matlab script showing how the data can be read and manipulated is provided. Please see the ‘airfoilLES_README.pdf’ file for more information. We recommend using the ‘airfoilLES_example.zip’ file as an entry point to the dataset.;The dataset is part of “A database for reduced-complexity modeling of fluid flows” (see references below) and is intended to aid in the conception, training, demonstration, evaluation, and comparison of reduced-complexity models for fluid mechanics. The paper introduces the flow setup and computational methods, describes the available data, and provides an example of how these data can be used for reduced-complexity modeling. Users of these data should cite the papers listed below.

2-D Coanda Airfoil with Tangential Wall Jet. This web page provides data from experiments that may be useful for the validation of turbulence models. This resource is expected to grow gradually over time. All data herein arepublicly available.

This database includes the flow-velocity data presented in the companion paper "Experimental investigation of turbulent coherent structures interacting with a porous airfoil", which has been published in the journal "Experiments in Fluids". The measurements refer to three free-stream velocities, namely 20 m/s, 30 m/s, and 40 m/s, and to three different wing-profile configurations, namely a "solid", "porous", and "melamine" airfoil (as described in the paper). The data include 2D flow-velocity maps (expressed in m/s) for the streamwise and upwash velocity component (considering the reference system described in the paper) and two arrays of x- and y-coordinates for the definition of the spatial locations of the measurement points. Each velocity map refers to a different time step, for a total of 8000 time steps (1 s of acquisition with a sampling rate of 8 kHz). The present database is suitable for the application of the Proper Orthogonal Decomposition (POD) technique, as shown in the paper.

Overview Airfoil Performance Degradation due to Roughness and Leading-edge Erosion. The zip file contains analysis, charts, and photos.

2-D Coanda Airfoil with Tangential Wall Jet. This web page provides data from experiments that may be useful for the validation of turbulence models. This resource is expected to grow gradually over time. All data herein arepublicly available.

The present experimental work is motivated by the need for additional insight into the vortex-induced vibrations (VIV) of airfoils at high angle of attack from an aerodynamic perspective. Airfoil NACA643418 is set to periodic pitching motion. This experimental dataset temporarily contains surface pressure measurements of a pitching airfoil with a mean angle of attack set at 170 degrees, pitching frequency of 2 Hz, and pitching amplitude of 1o degrees.

Airfoil data DU40_A17 for the NREL 5MW wind turbineMatlab program for cross-section parameter calculationMathematic program for eigenvalue calculationand FE model of the tapered blade

Averaged lift and drag coeffficients of a DU00-W-212 profile in turbulent inflow generated with an active grid at Reynolds numbers 500,000 and 900,000. The inflow pattern was mimicked from measurements a the blade with a 5-hole pressure probe performed in teh DanAero project.

Data is obtained with a three-component load cell and via integration of 48 scanned pressure tabs along the chord. Standard wind tunnel corrections according to Allen & Vincenti are applied.

Data sets 203, 204, 210, 211: flow tripped on the surface at 1.5% chord on upper airfoil side, 10% chord on lower airfoil side Data sets 203, 211, 225, 230: measured starting at positive angles of attack (AOA) to negative AOAs Data sets 204, 210, 224, 239: measured starting at negative angles of attack (AOA) to positive AOAs

The experiment was performed within in the EU-funded project AVATAR (www.eera-avatar.eu).

The response of a NACA0012 airfoil impacted by viscous vortical gusts at low Reynolds numbers is investigated performing Direct Numerical Simulations of the two-dimensional incompressible flow. This database contains the time history of the aerodynamic force coefficients of the airfoil during the interaction with the vortical gust. The airfoil, set at a fixed angle of attack alpha, is impacted by Taylor/Lamb-Oseen vortical gust, which are characterized by a diameter D, a intensity v_0m, and a vertical separation h. Direct Numerical Simulations are run for a range of values for the angle of attack, the size and intensity of the vortical gust, and the vertical separations. All simulations are run at a fixed Reynolds number Re=1000, based on the airfoil chord c and the free-stream velocity U_∞.

More details on the database and the corresponding simulations can be found in Martínez-Muriel & Flores (2020), Analysis of vortical gust impact on airfoils at low Reynolds number, J. Fluids and Struct, 99.

Contents
The database consist on a single ASCII file for each case. After a short, self-explanatory header, each file has 7 columns with the following data:

• time, t U_∞/c
• cl: lift coefficient, c_l
• cd: drag coefficient, c_d
• cm: coefficient of moments with respect to c/4, c_m
• dcl: perturbation of c_l with respect to steady state value, ∆c_l
• dcd: perturbation of c_d with respect to steady state value, ∆c_d
• dcm: perturbation of c_m with respect to steady state value, ∆c_m

Reference time (t=0) is taken as the time at which the center of the vortical gust reaches the position of the leading edge of the airfoil (if advected at a velocity U_∞).

Nomenclature
The names of the files will follow the acronym t_AaYyDdVv.txt, where the lowecase letters are placeholders for:

The main goal of this research is to experimentally investigate the unsteady aerodynamics of a static airfoil at large angles of attack (AoA), with a focus on the wake flow dynamics, vortex shedding characteristics and airfoil loading. This dataset contains the experimental measurement of a static DU91-W2-150 airfoil in a closed wind tunnel. This experimental study tested the airfoil under a wide range of AoA from 0◦ to 310◦ at three Reynolds numbers (Re) from 2×10^5 to 8×10^5. Pressure on the airfoil surface was measured and Particle Image Velocimetry (PIV) measurements were conducted to capture the flow field in the wake.

A NACA 0018 airfoil in freestream velocity is oscillated in longitudinal, transverse, and angle-of-attack directions with respect to the freestream velocity, known as surge, plunge, and pitch. The lift-based equivalence method introduces phase shifts between these three motions to construct in-phase sinusoidal components for maximum lift, waveform construction. Lift cancellation is also determined with the exact negative pitch and plunge motion amplitudes found from the equivalence method to achieve out-of-phase wave destruction. Lift cancellation occurs when a combination of these motions is sought to obtain a constant lift magnitude throughout the oscillation cycle. To achieve both equivalence and cancellation of lift, a prescribed pure pitch amplitude through the Theodorsen theory equates the corresponding equivalent plunge amplitude and pitch-plunge phase shift. These Theodorsen, linear superposition findings of pitch-plunge are leveraged toward the Greenberg theory to determine a closed-form, surge-pitch-plunge solution through the addition of a surge-plunge phase shift and optimal surge amplitude for lift cancellation. The lift cancellation surge-pitch-plunge amplitudes define the equivalence amplitude investigated here and theoretically limit the experiment to combinations of the first lift harmonic of the Greenberg theory. The analytical results are then compared with experimental lift force measurements and dye visualization. The normalized lift differences due to unsteady wake and boundary-layer behavior are examined to explore the extents of the Greenberg theory for these cases of lift-based equivalence and cancellation.

{"references": ["R.B. Green, M. Giuni, Dynamic stall database R & D 1570-AM-01: Final Report. 2013 DOI: 10.5525/gla.researchdata.464", "J. M. Janiszewska, R. F. Ramsay, M. J. Hoffman, G. M. Gregorek Effects of Grit Roughness and Pitch Oscillations on the LS(1)-0417MOD Airfoil. 1996 NREL/TP-442-7819", "M. J. Hoffman, R. F. Ramsay, G. M. Gregorek Effects of Grit Roughness and Pitch Oscillations on the NACA 4415 Airfoil. 1996 NREL/TP-442-7815", "R. F. Ramsay, M. J. Hoffman, G. M. Gregorek Effects of Grit Roughness and Pitch Oscillations on the S809 Airfoil. 1995 NREL/TP-442-7817", "A. Gonzalez-Salcedo, M. Aparicio-Sanchez, X. Munduate, R. Palacios, J.M.R. Graham, O. Pires, and B. Mendez. A Computationally-Efficient Panel Code for Unsteady Airfoil Modelling Including Dynamic Stall, 35th Wind Energy Symposium, AIAA SciTech Forum, (AIAA 2017-2000) \tDOI: https://doi.org/10.2514/6.2017-2000", "Hendrik Hei\u00dfelmann et al. Experimental airfoil characterization under tailored turbulent conditions. 2016 J. Phys.: Conf. Ser. 753 072020 \tDOI: https://doi.org/10.1088/1742-6596/753/7/072020"]} A selection of four different unsteady aerodynamic experiments have been done to prepare a database which will serve for the analysis, investigation and tool validation of airfoil unsteady behavior of wind turbine blades. The four experiments and selected data are: University of Glasgow dynamic stall experiments: NACA0015 and NACA0030 airfoils tested at sinusoidal type motion of the pitch. NREL OSU experiments: LS(1)0417MOD, NACA4415 and S809 airfoils tested at sinusoidal type motion of the pitch. CENER unsteady airfoil pitching and flapping tests at DTU: NACA643-418 airfoil tested at sinusoidal type motion of the pitch, the flap and combined pitch and flap. ForWind airfoil tests under tailored inflow turbulence: DU00W212 airfoil with laminar flow, open grid condition and one sinusoidal dynamic grid condition.

The INTEGRATE (Inverse Network Transformations for Efficient Generation of Robust Airfoil and Turbine Enhancements) project is developing a new inverse-design capability for the aerodynamic design of wind turbine rotors using invertible neural networks. This AI-based design technology can capture complex non-linear aerodynamic effects while being 100 times faster than design approaches based on computational fluid dynamics. This project enables innovation in wind turbine design by accelerating time to market through higher-accuracy early design iterations to reduce the levelized cost of energy. INVERTIBLE NEURAL NETWORKS Researchers are leveraging a specialized invertible neural network (INN) architecture along with the novel dimension-reduction methods and airfoil/blade shape representations developed by collaborators at the National Institute of Standards and Technology (NIST) learns complex relationships between airfoil or blade shapes and their associated aerodynamic and structural properties. This INN architecture will accelerate designs by providing a cost-effective alternative to current industrial aerodynamic design processes, including: - Blade element momentum (BEM) theory models: limited effectiveness for design of offshore rotors with large, flexible blades where nonlinear aerodynamic effects dominate - Direct design using computational fluid dynamics (CFD): cost-prohibitive - Inverse-design models based on deep neural networks (DNNs): attractive alternative to CFD for 2D design problems, but quickly overwhelmed by the increased number of design variables in 3D problems AUTOMATED COMPUTATIONAL FLUID DYNAMICS FOR TRAINING DATA GENERATION - MERCURY FRAMEWORK The INN is trained on data obtained using the University of Marylands (UMD) Mercury Framework, which has with robust automated mesh generation capabilities and advanced turbulence and transition models validated for wind energy applications. Mercury is a multi-mesh paradigm, heterogeneous CPU-GPU framework. The framework incorporates three flow solvers at UMD, 1) OverTURNS, a structured solver on CPUs, 2) HAMSTR, a line based unstructured solver on CPUs, and 3) GARFIELD, a structured solver on GPUs. The framework is based on Python, that is often used to wrap C or Fortran codes for interoperability with other solvers. Communication between multiple solvers is accomplished with a Topology Independent Overset Grid Assembler (TIOGA). NOVEL AIRFOIL SHAPE REPRESENTATIONS USING GRASSMAN SPACES We developed a novel representation of shapes which decouples affine-style deformations from a rich set of data-driven deformations over a submanifold of the Grassmannian. The Grassmannian representation as an analytic generative model, informed by a database of physically relevant airfoils, offers (i) a rich set of novel 2D airfoil deformations not previously captured in the data , (ii) improved low-dimensional parameter domain for inferential statistics informing design/manufacturing, and (iii) consistent 3D blade representation and perturbation over a sequence of nominal shapes. TECHNOLOGY TRANSFER DEMONSTRATION - COUPLING WITH NREL WISDEM Researchers have integrated the inverse-design tool for 2D airfoils (INN-Airfoil) into WISDEM (Wind Plant Integrated Systems Design and Engineering Model), a multidisciplinary design and optimization framework for assessing the cost of energy, as part of tech-transfer demonstration. The integration of INN-Airfoil into WISDEM allows for the design of airfoils along with the blades that meet the dynamic design constraints on cost of energy, annual energy production, and the capital costs. Through preliminary studies, researchers have shown that the coupled INN-Airfoil + WISDEM approach reduces the cost of energy by around 1% compared to the conventional design approach. This page will serve as a place to easily access all the publications from this work and the repositories for the software developed and released through this project.

This dataset includes the experimentally obtained airfoil polars of 4 airfoils optimised for inclined struts of a multi-megawatt VAWT. The data and measurement campaign are discussed in the PhD thesis of D. De Tavernier.

This dataset includes the experimentally obtained airfoil polars of 3 airfoils optimised for a multi-megawatt VAWT including individual blade pitching. The data and measurement campaign are discussed in the PhD thesis of D. De Tavernier.

Dataset for the ABIBA experiments. The data was collected at the Delft University of Technology's Low Turbulence Tunnel in summer of 2020.

Data includes:

·
Report summarizing results

·
Geometry and pressure tap locations for the base airfoil (DU-00 W2-401)

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Geometry and pressure tap locations for custom slat profile

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Final experimental polars

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Cp data for slat and profile for each testing configuration

Pictures of measurement setup

Measurement is conducted at a Re: 1.5 x 106 and 2.0 x 106

The base airfoil is measured in three configurations; clean, tripped, and with vortex generators. There are 9 different slat configurations as discussed in the included report. Each are measured in clean and tripped conditions.