Below, is the 1880 and 4680 a typo, or am I totally missing something.
I thought it should be 1800, and 1800*2.3 = 4140 / 135 = 30.67.  Now,
don't think I'm just being picky...I'm not....I'm just trying to
understand.

---
Shannon Knoepflein   <--->   kycshann@kyol.net


<<The forward CG is at 27.7", the center of lift (CL) is 25% MAC (mean
aerodynamic chord) which is about 30" and the tail MAC at about 165. Assume the airplane is balanced on the center of lift, the forward down
force
is 2.3x1880 =  4680 / 135 = 35 pounds of down force on the tail.  >>

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