15.6: Display Distribution of ai
The pressure balance flow in different places of the wing (mainly at the wing
tips) causes a certain reduction of the angle of attack along the wingspan. One
calls this angle reduction the induced angle of attack ai.
The effective angle of attack is then alpha_eff
= alpha_total - alpha_induced.
If one knows the lift coefficient Cl and the
induced drag Cdi, one can compute the induced angle of attack according to the
following formula.
ai = Cdi / Cl (in radian)
or
ai = Cdi / Cl *180 / pi (in degree)
Select this button to display the curve of the induced angle of attack in the
2D-graphic.
The picture below illustrates this function.