In article .com,
"Tony" wrote:

I suspected most "lift" or at least delta momentum was generated near
the leading edge, so having a long chord didn't contribute much at low
airspeeds.

I do appreciate the effects of the burble or vortex at the wing ends
and the advantages of winglets, at least at higher air speeds.


High aspect ratio reduces induced drag, which helps aircraft flying at
slow indicated airspeed.

The formula is: CDi = CL**2/(pi*A*e), whe

CDi = induced drag coefficient
CL = lift coefficient
pi = 3.141759..........
A = aspect ratio = wingspan**2/wing area
e = wing shape efficiency (elliptical lift distribution is best;
constant chord is least)