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# True Anomaly, `nu`[`vecn,vecr`]

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Equation / Last modified by Administrator on 2017/10/19 07:05
`nu = `

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MichaelBartmess.True Anomaly, `nu`[`vecn,vecr`]

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77729901-e4b6-11e3-b7aa-bc764e2038f2

The **True Anomaly** calculator computes the True Anomaly, ν, of an orbit based on the eccentricity and radius vectors.

**INSTRUCTIONS:** Enter the following:

**E**This is the eccentricity vector in comma separate values (e.g. 1,2,3)**R**This is the orbital radius vector

**True Anomaly (ν):** The True Anomaly is returned in degrees. However, this can be automatically converted to other angle units via the pull-down menu.

**Related Calculators:**

- Compute True Anomaly from Eccentricity and Eccentric Anomaly
- Vector Magnitude
- Vector Dot Product
- Vector Calculator

### The Math / Science

The True Anomaly is the angle between the direction of periapsis and the current position of the body.

This equation,

**True Anomaly, `nu`[`vecn,vecr`]**, references 2 equations/constants.**Equations and Constants **