DATA AVAILABLE:

- Airfoil shape

Experiments:
- Lift and Drag Coefficients
- Moment Coefficient

XFOIL Computations:
- Lift, Drag and Moment Coefficients

- Skin Friction and Pressure Distributions - Angle of Attack = 06.0 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 10.0 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 12.0 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 14.0 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 16.0 deg.
- Skin Friction and Pressure Distributions - Angle of Attack = 18.0 deg.

EllipSys2D Computations:

Not computed yet for this Reynolds number!

FIGURES AVAILABLE: (PostScript files)

- Airfoil shape

- Lift Coefficient
- Drag Coefficient
- Moment Coefficient

- Pressure Distribution - Angle of Attack = 06.0 deg.
- Pressure Distribution - Angle of Attack = 10.0 deg.
- Pressure Distribution - Angle of Attack = 12.0 deg.
- Pressure Distribution - Angle of Attack = 14.0 deg.
- Pressure Distribution - Angle of Attack = 16.0 deg.
- Pressure Distribution - Angle of Attack = 18.0 deg.

- Skin Friction Distribution - Angle of Attack = 06.0 deg.
- Skin Friction Distribution - Angle of Attack = 10.0 deg.
- Skin Friction Distribution - Angle of Attack = 12.0 deg.
- Skin Friction Distribution - Angle of Attack = 14.0 deg.
- Skin Friction Distribution - Angle of Attack = 16.0 deg.
- Skin Friction Distribution - Angle of Attack = 18.0 deg.