Patent ID: 8262030

Claim:
A vehicle comprising; a wing; a twistable portion on the wing; and a control system for implementing a first twist distribution and a second twist distribution in the twistable portion of the wing; wherein the control system is able to vary twist amount for the first and second twist distributions to implement a twist distribution based, at least in part, upon an equation, the equation being ω ⁡ ( θ ) = F ⁡ ( π / 2 ) - F ⁡ ( θ ) F ⁡ ( π / 2 ) - F ⁡ ( 0 ) where F ⁡ ( θ ) = ∑ n = 1 ∞ ⁢ w n [ 4 ⁢ b C ~ L , αC ⁡ ( θ ) + n sin ⁡ ( θ ) ] ⁢ sin ⁡ ( n ⁢ ⁢ θ ) w n = 1 2 ⁢ π ⁢ ∫ θ = 0 π ⁢ c ⁡ ( θ ) ⁢ C ~ Ld ⁢ ( θ ) bC L ⁢ sin ⁡ ( n ⁢ ⁢ θ ) ⁢ ⅆ θ and where ω(θ) is the twist distribution b is a wingspan, {tilde over (C)} L,α is an airfoil section lift slope, c(θ) is a local airfoil section chord length at θ, θ is equal to cos −1 (−2z/b) where z is a spanwise coordinate and b is a wingspan, {tilde over (C)} Ld (θ) is a target airfoil section lift coefficient distribution that is to be produced over the wingspan, and C L is a lift coefficient of the wing.