>Yes, but also .... what's happening (for a fixed wing span) is a  trade off 
>between wing loading and induced drag. Re (at least for DLG chords and  up) is 
>a variable but not the dominant one.
>
>As you increase aspect ratio (reduce chord for a fixed wing span),  induced 
>drag goes down but wing loading goes up. The wing loading will  eventually 
>degrade your sink rate more than the aspect ratio improves it.  Although the 
wing 
>weight scales with area, the total weight does not (fuselage,  tail surfaces, 
>ancillary equipment). Re will hurt here as well (both Cd and Cl)  but it's 
>primarily the loading (except perhaps at very small chords).
>
>On  the other end, lower aspect ratio gives a lower wing loading but 
>increased  induced drag (Cl^2/(Pi * AR).

Dave, you should know that for a fixed wing span, you need to be talking about 
total drag, not a drag coefficient, because you are changing the wing area when 
you change the aspect ratio. Total induced drag depends on the span only (for a 
constant weight and flight speed). Changing aspect ratio with a fixed span does 
not affect induced drag (if we ignore that the weight of the structure 
changes). 
Induced drag is proportional to the span loading squared (the formula below is 
obtained by manipulating the one above Cdi=Cl^2/(Pi*AR)):

D = (W/L)^2/(Pi*q), where q = rho*V^2/2

Therefore with a fixed span, you can easily find a wing area that gives you the 
best L/D ratio (parasite drag = induced drag). But that maybe still not the 
best 
design depending on your objectives. The main trade-off variables are min 
flight 
speed (affects turn radius), best L/D ratio, and high speed performance, all of 
which are directly affected by the wing area. Obviously, reducing the weight 
and 
parasite (fuselage, tail) drag allows to improve all of the criteria because 
the 
optimum wing area becomes smaller.

Comments and corrections are most welcome.
Regards,
Oleg.

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