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Static TEFlap TL-190-82 Re 3.3M

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The benchmark is public for the validation of aerodynamic codes and models of 2D airfoils including deformable geometries. The cases of the benchmark are static flap configurations in clean and transition conditions.


Produce the best estimate of the aerodynamic polars of the TL-190-82 airfoil with a TE flap at different static deployments.

Data Accessibility

The benchmark is offered to participants of AVATAR, and provided as public in the windbench platform by the University of Stuttgart.

Input data

The input data for simulating the TL-190-82 airfoil with a static flap are:
•    Airfoil geometry
•    Airfoil chord = 0.6 m
•    Tripped conditions = 5% chord
•    TE flap geometry = Rigid 10% chord
•    Flap angle = -10º, -5º, 0º, 5º, 10º
•    Wind speed = 82.5 m/s
•    Angle of attack range (see experimental data)

Validation data

The experimental data available in each file (see experimental data):
•    Angle of attack (AoA)
•    Lift force coefficient (Cl)
•    Drag force coefficient (Cd)

The name of the files have the following information:
•    TL190-82: Reference to the TL-190-82 airfoil
•    Re3_3: Reynolds number 3.3 Mio.
•    Flap: Flap angle
•    N10, N5, 0, 5, 10: -10º, -5º, 0º, 5º, 10º
•    C, T: Clean, Tripped

Model runs

The user is free to optimize the simulation settings as desired.

Output data

The requested output data consists on different files for each static flap configuration of the airfoil, in clean or forced transition conditions. For each case, the output point in each line of the file should provide angle of attack, Cl and Cd.

An example for the output template is included (see Output template). The name of the output files have the following information apart of the name of the experimental data simulated:
•    CENER: Name of the data provider
•    WMB: Name of the code
•    r0, r1, r2...: Number of revision