Induced Angle of Attack Calculator

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Posted by Dinesh on

Use this aerodynamics calculator to calculate the induced angle of attack for your aerodynamics problems.

Calculate Induced Angle of Attack

Lift coefficient (CL) :
Aspect ratio (A):
∝i :

Formula:

∝i = CL / ( π × A )

where,
CL - Lift coefficient
π - 3.142857142857143
A - Aspect ratio
∝i - Induced angle of attack (rad)
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