Data for: Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor (doi:10.18419/darus-2191)

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Data for: Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor

doi:10.18419/darus-2191

DaRUS

2021-10-21

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Huang, Doudou; Gagnon, Louis, 2021, "Data for: Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor", https://doi.org/10.18419/darus-2191, DaRUS, V1

Data for: Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor

doi:10.18419/darus-2191

Huang, Doudou (Universität Stuttgart)

Gagnon, Louis (Universität Stuttgart)

DaRUS

Keßler, Manuel

Gagnon, Louis

2021-10-08

https://doi.org/10.18419/darus-2191

Engineering, Cycloidal Rotor, Dynamically Camber Morphing, Cambered NACA Profile, Trailing Edge Deformation, Leading Edge Morphing

OpenFOAM simulation case files and results accompanying the article having the same title are included. The pressure, velocity and vorticity fields could be visualized by using Paraview.<br> The simulation of the last rotor revolution of each case can be reproduced by running the restartLastCycle.sh script.<br> The supplementary cases which are not documented in the cited paper are described in the linked Master Thesis (see metadata).

Huang, D. and Gagnon, L. « Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor », IOP Conf. Ser.: Mater. Sci. Eng. 1226 012014, 2022

10.1088/1757-899X/1226/1/012014

Huang, D. and Gagnon, L. « Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor », IOP Conf. Ser.: Mater. Sci. Eng. 1226 012014, 2022

Huang, D., « Evaluate the Performance of a Camber Controlled Cycloidal Rotor », Master's Thesis, Stuttgart University, Stuttgart, Germany, 2021.

10.18419/opus-12006

Huang, D., « Evaluate the Performance of a Camber Controlled Cycloidal Rotor », Master's Thesis, Stuttgart University, Stuttgart, Germany, 2021.

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LE_0.10-0.040_0.10-0.040.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 4% at position p = 0.1

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LE_0.30-0.020_0.30-0.020.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 2% at position p = 0.3

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LE_0.30-0.020_0.30-0.060.tar.bz2

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OpenFOAM simulation results: asymmetric leading edge camber with 2% camber at top and 6% camber at bottom, p=0.3

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LE_0.30-0.040_0.30-0.040.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 4% at position p = 0.3

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LE_0.30-0.060_0.30-0.020.tar.bz2

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OpenFOAM simulation results: asymmetric leading edge camber: 6% camber at top and 2% camber at bottom, p=0.3

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LE_0.30-0.060_0.30-0.060.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 6% at position p = 0.3

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LE_0.30-0.080_0.30-0.080.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 8% at position p = 0.3

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LE_0.30-0.120_0.30-0.120.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 12% at position p = 0.3

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LE_0.50-0.040_0.50-0.040.tar.bz2

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OpenFOAM simulation results: symmetric leading edge camber of 4% at position p = 0.5

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Mesh description.7z

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Pointwise file and exported polyMesh for OpenFOAM

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naca_0.20-0.120_0.20-0.120.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 12% at position p = 0.2

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naca_0.30-0.120_0.30-0.120.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 12% at position p = 0.3

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naca_0.40-0.040_0.40-0.040.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 4% at position p = 0.4

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naca_0.40-0.080_0.40-0.080.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 8% at position p = 0.4

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naca_0.40-0.080_0.40-0.160.tar.bz2

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OpenFOAM simulation results: asymmetric NACA camber with 8% camber at top and 16% camber at bottom, p=0.4

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naca_0.40-0.100_0.40-0.100.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 10% at position p = 0.4

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naca_0.40-0.120_0.40-0.120.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 12% at position p = 0.4

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naca_0.40-0.140_0.40-0.140.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 14% at position p = 0.4

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naca_0.40-0.160_0.40-0.080.tar.bz2

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OpenFOAM simulation results: asymmetric NACA camber with 16% camber at top and 8% camber at bottom, p=0.4

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naca_0.40-0.160_0.40-0.160.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 16% at position p = 0.4

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naca_0.50-0.120_0.50-0.120.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 12% at position p = 0.5

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naca_0.60-0.120_0.60-0.120.tar.bz2

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OpenFOAM simulation results: symmetric NACA camber of 12% at position p = 0.6

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no_camber.tar.bz2

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OpenFOAM simulation results: baseline case with symmetric NACA0015 airfoils

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pointDisplacement_scripts.tar

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python scripts used for pointDisplacement file generation

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Results_Summary.pdf

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The thrust, power and efficiency results of all cases are concluded.

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TE_0.20-0.100_0.20-0.100.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 10% at position p = 0.2

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TE_0.40-0.100_0.40-0.100.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 10% at position p = 0.4

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TE_0.60-0.100_0.60-0.100.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 10% at position p = 0.6

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TE_0.70-0.040_0.70-0.040.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 4% at position p = 0.7

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TE_0.70-0.080_0.70-0.080.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 8% at position p = 0.7

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TE_0.70-0.080_0.70-0.160.tar.bz2

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OpenFOAM simulation results: asymmetric trailing edge camber with 8% camber at top and 16% camber at bottom, p=0.7

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TE_0.70-0.100_0.70-0.100.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 10% at position p = 0.7

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TE_0.70-0.120_0.70-0.120.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 12% at position p = 0.7

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TE_0.70-0.140_0.70-0.140.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 14% at position p = 0.7

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TE_0.70-0.160_0.70-0.080.tar.bz2

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OpenFOAM simulation results: asymmetric trailing edge camber with 16% camber at top and 8% camber at bottom, p=0.7

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TE_0.70-0.160_0.70-0.160.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 16% at position p = 0.7

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TE_0.80-0.100_0.80-0.100.tar.bz2

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OpenFOAM simulation results: symmetric trailing edge camber of 10% at position p = 0.8

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