`nu = arccos( (cos(E) - e) / ( 1-e*cos(E)) )`

Enter a value for all fields

The True Anomaly calculator computes the True Anomaly (ν) of an orbit from the inputs:

• E - the eccentricity anomaly
• e - eccentricity

True Anomaly (ν): The True Anomaly is the angle between the direction of periapsis and the current position of the body.