A constant chord wing whose cross$-$section is shown in the Figure will be tested in the wind

tunnel at several airspeeds at sea level conditions and at such low speeds that the flow is effectively incom$-$

pressible. The position of the wing box indicated in the Figure can be moved fore or aft to change the

wing shear center position and the offset distance between the shear center and the aerodynamic center. For

instance, when the shear center is at the mid$-$chord the offset distance is equal to c$/4,$ where c is the chord.

Preliminary wind tunnel tests show that the wing divergence dynamic pressure is $100$ lb$/$ft$2$ at this wing box

position. Aerodynamic theory predicts that the ratio of CMac to CL$,$ is $0\mathrm{.}075$ and the wing lift slope is $4$

$($the fact that it is not $2$ is due to finite span effects$).$ The wing planform area is $10$ ft$2.$ The section angle of

attack is set to $3.$