Folie 17 von 21
Notizen:
In the third slide of this series, the pressure distribution at an angle of attack of 36 degrees is shown.
In the upper diagram for the aerofoil without flaps the flow separation has spread even further and the effect of the trailing vortices (which is basically a virtual decrease in the angle of attcack) cannot prevent this even in these areas.
In the lower diagram, the further decrease of the high lift generation is visible as well, yet, in front of the flaps there is still the area with a fairly large lift generation.
