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    Re: Additional corrections to the sextant altitude in air navigation
    From: Gary LaPook
    Date: 2007 Dec 14, 03:48 -0800
    Gary LaPook writes:

    The simplified formula for the coriolis correction is 2.62 times the ground speed (in 100s of knots) times the sine of the latitude gives you the correction in minutes of altitude. so, at a 100 knot ground speed the maximum correction would be 2.62' if the shot were taken over one of the poles and zero if taken at the equator.

    I am attaching pages from the current U.S. Air force Navigation Manual, AFPAM 11-216, which explains the sextant corrections.

    Though not truly "corrections" for errors in the observation, flight practice is to use "Motion Of The Body" correction instead of using the actual time of the sight and "Motion Of The Observer" correction instead of advancing the LOPs to a common time. Go back to the "Flight Navigation" thread last March for posts on this subject.


    Andres Ruiz wrote:
    Additional corrections to the sextant altitude in air navigation

    I am interested about celestial navigation used in aircraft. Although for me is impracticable, my interest is scientific.

    What are the additional corrections to the sextant altitude in air navigation?

    [NavList 4304]  attached a table from H.O 249 containing the coriolis correction, not applicable for speed V < 50 kt

    I know in our list there are some air pilots that could answer me.

    Some recommended links and books are also welcoming


    Navigational Algorithms


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    File: 104310.pages-from-afpam11-216.pdf
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