Dave,

>OK, we've got a nomenclature difference (it's always the communication  
>issues, isn't it?)

In my original message I said the induced drag is proportional to SPAN LOADING, 
not wing loading, for a fixed span wing. That is really all I am trying to show 
you:

Di = (W/L)^2 / (Pi*q), where

W = weight, L = span, q = rho*V^2/2


>Sorry for the digression but with this sorted out, the result is  
>mathematically the same. The reason I prefer to keep it in the "wing loading"  
form is 
>that the scaling is a bit more apparent (to me).

You can keep it in any form you want, the result is the same, total induced 
drag 
is not dependant on the AR for a fixed span. This is really a simple 
aerodynamic 
axiom that does need to be argued about. I guess I am not a high enough 
authority to take my word on it :-)

>For a fixed span, as aspect ratio increases, the wing  loading does not go up 
>as fast as Cavg goes down so Cavg wins. For a fixed Cavg,  as aspect ratio 
>increases, wing loading will go up so drag should increase  (??)

By using chord and wing loading you are just clouding the issue. Yes, W/L = 
W*C/S, but you cannot change C (chord) without changing S (area) for a fixed 
span. It is still SPAN LOADING, Weight/Span. And yes, wing loading DOES go up 
as 
fast as the chord goes down. Change AR all you want, you are not changing SPAN 
LOADING. This is just elementary algebra actually, not even aerodynamics.

>My assumption is that you have to look at the entire package.

I agree. I was only correcting you on one point. Total induced drag does not 
depend on the AR, only on the span, weight, speed. I hope you can work out the 
algebra and convince yourself in that.

Best regards,
Oleg.

PS. Apologies to the list for dragging this issue so far. I was not really 
contributing to the original topic here, just could not let the incorrect 
statement go :-0

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