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what is best simpified lift distribution methode for GA airplanes?

what is best simpified lift distribution methode for GA airplanes?

what is best simpified lift distribution methode for GA airplanes?

(OP)
Hello people?

I have got a question. For a design of a sportplane I have to define the load distribution along the wingspan. I have found some different methods but I would like to use the most close approximation which I can make without using some airstream simulation programs. Or wind tunnel tests.
 
The wing is unswept , tapered and got flaps, flapperons, twist, and a fuselage in the middle between the wings.
I have found a method developed by Schrenk. He uses a average between a constant cl and a elliptic cl distribution. But

But I would like approximate the lift distribution and the tosionmoment along the wing span caused by cm.

If I use for a certain station along the span the cm value for the same angle of attack as the 2d cl. I say in other words that the lift reduction to the tip is caused by a reduction of angle of attack.. .. is this thinking correct? Is there somebody who knows a better method for estimate the lift distribution?

Thanks,

Tim

RE: what is best simpified lift distribution methode for GA airplanes?

yeah, that's the approach i've seen too ... distribute Cm like the schrenk distribution.

there might be something on the FAA site, an AC for FAR23 loads

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