Use this aerodynamics calculator to calculate the induced angle of attack for your aerodynamics problems.
Formula:
∝i = CL / ( π × A )
where,CL - Lift coefficient
π - 3.142857142857143
A - Aspect ratio
∝i - Induced angle of attack (rad)
Induced Angle of Attack Calculator
Calculate Induced Angle of Attack
CL - Lift coefficient
π - 3.142857142857143
A - Aspect ratio
∝i - Induced angle of attack (rad)