Folie 18 von 21
Notizen:
In this picture the calculated lift coeffient is depicted over the angle of attack.
The lift coefficient is calculated by integrating the pressure measurement of all measuring rows of upper and lower surface.
The curve resembles that which I showed earlier which was obtained by measuring the lift and drag directly with a balance.
Again, the curve for the aerofoil without flaps shows the sudden drop in lift generation, whereas the one with flaps shows nearly the desired behaviour.
