How to determine individual wing loading of a triplane for stress analysis?
I understand that a monoplane must be able to withstand the weight of a plane x a load factor, say n=4, for a standard flight envelope, and also asymetrical loading.
What about triplanes?
Should each wing carry 1/3 the load?
Assuming 1 deg decalage each for the 2nd and 3rd top wings, they will stall before the bottom wing.
But.... you could have a situation where the top wing is stalled and the bottom 2 wings see the full load of the plane
And... you could have a situation where the top 2 wings are stalled, and the bottom wing is subjected to the entire weight of the plane.
So.... how strong do you have to make each wing of a triplane? Of course, if the plane has struts, all 3 wings would be part of the equation.
My gut feeling is that the top wing should be 33% loading, middle wing 50% loading, and bottom wing 100% loading, and then model the wings as 3 joined cantilevered beams.
Is this correct?