RISØ-A1-21 AIRFOIL


Reynolds number = 1.6 x 10^6

Measured in the Velux wind tunnel (see Fuglsang, Dahl and Antoniou)

More details on computations and experimental facilities can be found in the Wind Turbine Airfoil Catalogue.




DATA AVAILABLE:

- Airfoil shape (Not available - Request here)

Experiments:
 - Lift, Drag and Moment Coefficients

- Pressure Distribution - Angle of Attack = 05.12 deg.
- Pressure Distribution - Angle of Attack = 08.29 deg.
- Pressure Distribution - Angle of Attack = 10.22 deg.
- Pressure Distribution - Angle of Attack = 12.31 deg.
- Pressure Distribution - Angle of Attack = 15.11 deg.
- Pressure Distribution - Angle of Attack = 17.88 deg.

XFOIL Computations:
 - Lift, Drag and Moment Coefficients

- Skin Friction and Pressure Distributions - Angle of Attack = 05.12 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 08.29 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 10.22 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 12.31 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 15.11 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 17.88 deg.

EllipSys2D Computations:

* Fully turbulent:
 - Lift, Drag and Moment Coefficients

- Pressure Distribution - Angle of Attack = 05.12 deg.
- Pressure Distribution - Angle of Attack = 08.29 deg.
- Pressure Distribution - Angle of Attack = 10.22 deg.
- Pressure Distribution - Angle of Attack = 12.31 deg.
- Pressure Distribution - Angle of Attack = 15.11 deg.
- Pressure Distribution - Angle of Attack = 17.88 deg.

- Skin Friction Distribution - Angle of Attack = 05.12 deg.
- Skin Friction Distribution - Angle of Attack = 08.29 deg.
- Skin Friction Distribution - Angle of Attack = 10.22 deg.
- Skin Friction Distribution - Angle of Attack = 12.31 deg.
- Skin Friction Distribution - Angle of Attack = 15.11 deg.
- Skin Friction Distribution - Angle of Attack = 17.88 deg.

* With transition model:
 - Lift, Drag and Moment Coefficients

- Pressure Distribution - Angle of Attack = 05.12 deg.
- Pressure Distribution - Angle of Attack = 08.29 deg.
- Pressure Distribution - Angle of Attack = 10.22 deg.
- Pressure Distribution - Angle of Attack = 12.31 deg.
- Pressure Distribution - Angle of Attack = 15.11 deg.
- Pressure Distribution - Angle of Attack = 17.88 deg.

- Skin Friction Distribution - Angle of Attack = 05.12 deg.
- Skin Friction Distribution - Angle of Attack = 08.29 deg.
- Skin Friction Distribution - Angle of Attack = 10.22 deg.
- Skin Friction Distribution - Angle of Attack = 12.31 deg.
- Skin Friction Distribution - Angle of Attack = 15.11 deg.
- Skin Friction Distribution - Angle of Attack = 17.88 deg.




FIGURES AVAILABLE: (PostScript files)

- Airfoil shape (Not available)

- Lift Coefficient
- Drag Coefficient
- Moment Coefficient

- Pressure Distribution - Angle of Attack = 05.12 deg.
- Pressure Distribution - Angle of Attack = 08.29 deg.
- Pressure Distribution - Angle of Attack = 10.22 deg.
- Pressure Distribution - Angle of Attack = 12.31 deg.
- Pressure Distribution - Angle of Attack = 15.11 deg.
- Pressure Distribution - Angle of Attack = 17.88 deg.

- Skin Friction Distribution - Angle of Attack = 05.12 deg.
- Skin Friction Distribution - Angle of Attack = 08.29 deg.
- Skin Friction Distribution - Angle of Attack = 10.22 deg.
- Skin Friction Distribution - Angle of Attack = 12.31 deg.
- Skin Friction Distribution - Angle of Attack = 15.11 deg.
- Skin Friction Distribution - Angle of Attack = 17.88 deg.





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