what is best simpified lift distribution methode for GA airplanes?

[TmB28]

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

 

[rb1957]

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