lift distribution without flaps at different angles of attack
Notes:
The diagram shows the lift distribution over the length of the aerofoil.
The different curves represent different angles of attack. Let’s look at the curve for 6 degrees angle of attack.
The points represents the lift coeffienct calculated for the seven measuring rows (please remember that we measured only one side and the other side is the mirror image). The lift distribution is what you would expect, namely that in the middle of the aerofoil most of the lift is generated. Let us take a look at the curve for 18 degrees, which is just below the critical angle of attack.
The total lift generated has increased to a maximum, of course. A small increase of the angle of attack lead to the dramatical drop in lift generation.
It is obvious, that in the middle of the aerofoil, the flow separation reduces the generated lift more drastically than in the lateral areas of the aerofoil.
There, lift generation remains fairly high because of the effect of the trailing vortices.