Jan:
I have checked several of the articles in IEEE pubs regarding the
design of A0A sensors and of several systems which emilate them.
The most popular method seems to me to be a separate comparison of
pressures above and directly below the wing, Pt/Pb. Then there is the
same differential available from the pitot system, Pp/Ps.
Three sources state there is a straightline relation ship between these
two variables which equate to the angle of the airflow above the angle
of stall. Since the stall angle is the same for any single wing loading,
('G', density altitude, etc) one should be able to calculate the
difference angle and display the safety margin pertaining at that
moment.
The best indicator is one which changes colour with degree of danger -
the numbers don't matter on takeoff from Mexico City or in an airshow,
only the approaching danger. That's what I've opted for.
Happy Landings
Ferg #A064
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