Mark,
would this arrangement work well enough with all predefined
flap setting? One would have to establish a base line
for example, one would start with say a Cl of 1.35 for max climbing
performance in 45 deg. bank and x flap setting. Would the system
respond true enough through out the usable Cl range and corresponding
flap settings with that established base line? I could see were this
arrangement would not correlate well at the other usable Cl number. I
really do not know and would like to find out.

On Jul 10, 7:31 pm, Marc Ramsey wrote:
Bill Daniels wrote:
I've wondered if pressure ports on the top and bottom of the fuselage nose
where the nose contours are at about 45 degrees to the airstream wouldn't
give about the same pressure diferential that could be used to compute AoA.

The factory AOA meter in my DG-600 uses cross-connected pairs of
fuselage static ports just above the wing root, one set just aft of the
leading edge, and another at roughly 50% chord. The meter appears to be
a slightly modified electronic vario.

Marc