DATA AVAILABLE:

- Airfoil shape (Not available - Request here)

Experiments:
- Lift, Drag and Moment Coefficients

- Pressure Distribution - Angle of Attack = 05.97 deg.
- Pressure Distribution - Angle of Attack = 08.81 deg.
- Pressure Distribution - Angle of Attack = 10.37 deg.
- Pressure Distribution - Angle of Attack = 13.45 deg.
- Pressure Distribution - Angle of Attack = 15.39 deg.
- Pressure Distribution - Angle of Attack = 19.34 deg.

XFOIL Computations:
- Lift, Drag and Moment Coefficients

- Skin Friction and Pressure Distributions - Angle of Attack = 05.97 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 08.81 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 10.37 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 13.45 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 15.39 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 19.34 deg.

EllipSys2D Computations:

* Fully turbulent:
- Lift, Drag and Moment Coefficients

- Pressure Distribution - Angle of Attack = 05.97 deg.
- Pressure Distribution - Angle of Attack = 08.81 deg.
- Pressure Distribution - Angle of Attack = 10.37 deg.
- Pressure Distribution - Angle of Attack = 13.45 deg.
- Pressure Distribution - Angle of Attack = 15.39 deg.
- Pressure Distribution - Angle of Attack = 19.34 deg.

- Skin Friction Distribution - Angle of Attack = 05.97 deg.
- Skin Friction Distribution - Angle of Attack = 08.81 deg.
- Skin Friction Distribution - Angle of Attack = 10.37 deg.
- Skin Friction Distribution - Angle of Attack = 13.45 deg.
- Skin Friction Distribution - Angle of Attack = 15.39 deg.
- Skin Friction Distribution - Angle of Attack = 19.34 deg.

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

- Pressure Distribution - Angle of Attack = 05.97 deg.
- Pressure Distribution - Angle of Attack = 08.81 deg.
- Pressure Distribution - Angle of Attack = 10.37 deg.
- Pressure Distribution - Angle of Attack = 13.45 deg.
- Pressure Distribution - Angle of Attack = 15.39 deg.
- Pressure Distribution - Angle of Attack = 19.34 deg.

- Skin Friction Distribution - Angle of Attack = 05.97 deg.
- Skin Friction Distribution - Angle of Attack = 08.81 deg.
- Skin Friction Distribution - Angle of Attack = 10.37 deg.
- Skin Friction Distribution - Angle of Attack = 13.45 deg.
- Skin Friction Distribution - Angle of Attack = 15.39 deg.
- Skin Friction Distribution - Angle of Attack = 19.34 deg.

FIGURES AVAILABLE: (PostScript files)

- Airfoil shape (Not available)

- Lift Coefficient
- Drag Coefficient
- Moment Coefficient

- Pressure Distribution - Angle of Attack = 05.97 deg.
- Pressure Distribution - Angle of Attack = 08.81 deg.
- Pressure Distribution - Angle of Attack = 10.37 deg.
- Pressure Distribution - Angle of Attack = 13.45 deg.
- Pressure Distribution - Angle of Attack = 15.39 deg.
- Pressure Distribution - Angle of Attack = 19.34 deg.

- Skin Friction Distribution - Angle of Attack = 05.97 deg.
- Skin Friction Distribution - Angle of Attack = 08.81 deg.
- Skin Friction Distribution - Angle of Attack = 10.37 deg.
- Skin Friction Distribution - Angle of Attack = 13.45 deg.
- Skin Friction Distribution - Angle of Attack = 15.39 deg.
- Skin Friction Distribution - Angle of Attack = 19.34 deg.