Okay, maybe I'm not too bright... I need to understand how you get reduced
load on the wafs with fuel in the outer wing. Assuming 6 pounds per gallon,
how does (for example) a 10 gallon wing tank reduce stress on the waf if
(lift issues aside) you maneuver in any direction, considering inertia and
mass, that the 60 pounds in each outer wing doesn't affect the load on the
wafs? 

If the fuel is in the wing stubs and/or a header tank, I could see how the
'load' on the wafs might be neutral (all things considered), but with moment
arm considerations, wouldn't hanging that 60 pounds or so out at the outer
wing increase the flex load at the waf? 

Just asking for a friend. The CG issue would (I would think) depend on
placement of the tanks - wing or tip - relative to the "normal" CG
calculations for the airframe.

Blue skies, calm winds.

Mark W
N952MW (res) still workin on it.

-----Original Message-----
From: KRnet [mailto:[email protected]] On Behalf Of Mike
Stirewalt via KRnet
Sent: Monday, December 14, 2020 5:34 PM
To: [email protected]
Cc: [email protected]
Subject: KR> Wing tanks

Larry said, 

> "Fuel in the outer wings also reduce the weight carried by the
W.A.F.'s."

That is so true.  Tip tanks, or outer wing tanks, carry with them great
advantages.  Not only do they carry weight without affecting CG to any
significant extent, but unloads stress at the wing root, making for a
more resiliant structure.  A third virtue, at least with tip tanks, is
their reduction of tip vortice drag, acting as winglets.

Mike
KSEE

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