MHB Flight path angle concept question

AI Thread Summary
A flight path angle of 356 degrees can be interpreted as 4 degrees when defined as the angle between the flight path vector and the horizon. This interpretation arises from the relationship that angles can be expressed in a circular manner, where 356 degrees is equivalent to a negative angle of -4 degrees. The discussion emphasizes the importance of the definition used for flight path angles, suggesting a standard range between -180 and +180 degrees. Additionally, a mathematical formula for calculating the flight path angle is provided, involving the true anomaly and eccentricity of the orbit. Understanding these definitions and calculations is crucial for accurate discussions on flight path angles.
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Can a flight path angle be 356 degrees?
 
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dwsmith said:
Can a flight path angle be 356 degrees?

Hi dwsmith, :)

Depends on the way it's defined I presume. If it's defined as, angle between the flight path vector and the horizon (refer >>this<<) then 356 degrees will be the same as 360-356=4 degrees.

Kind Regards,
Sudharaka.
 
Sudharaka said:
Hi dwsmith, :)

Depends on the way it's defined I presume. If it's defined as, angle between the flight path vector and the horizon (refer >>this<<) then 356 degrees will be the same as 360-356=4 degrees.

Kind Regards,
Sudharaka.

Originally it was -4 so I added 360 to get the positive. So I can then subtract and say it is positive?
 
dwsmith said:
Originally it was -4 so I added 360 to get the positive. So I can then subtract and say it is positive?

Where did you encounter this question and can you please tell us how the flight path angle is defined in the book that you use? I presume that it is defined as an angle in-between -180 and +180.
 
Sudharaka said:
Where did you encounter this question and can you please tell us how the flight path angle is defined in the book that you use? I presume that it is defined as an angle in-between -180 and +180.

$$
\gamma = \tan^{-1}\left(\frac{e\sin\nu}{1 + e\cos\nu}\right)
$$
where $\nu$ is the true anomaly and e is the eccentricity of the orbit.
 

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