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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.



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