1. Procedure
2. The oblique wing model used for analysis is shown in Figure 5. An aspect ratio of 10 was chosen with a taper ratio of 0.4 and a root chord of 7.5 feet. The corresponding wing area is 275.625 square feet. A dihedral angle of 1.25" is built into the wing, which helps to alleviate the load imbalance between the forward and aft swept sections of the wing when sweep is introduced. The airfoil section used is the supercritical airfoil OW 70-10-12, which has a 12% maximum thickness-to-chord ratio [13]. Two outboard ailerons between the 55% and 85% semi-span stations are incorporated for roll control. The hinge line is at the 70% chord line. The left and right ailerons have equal and opposite deflections 6 (value of which is input and held constant for each computational run), a positive aileron deflection being defined as right aileron down.
3. The wing structural box was chosen to extend from the 10% to 70% chord lines, and from midspan to 90% semispan for both halves of the wing. The depth and camber of the box are taken to be the airfoil depth and camber. A typical graphitelepoxy was selected for the composite material of the wing box skin, and a 90'1-45"/+45"/0° stacking sequence was used for the skin laminate (90" direction is parallel to the wing's leading edge). The distribution of the laminate is taken to be 60% of the skin thickness in the 90" direction, 15% each in the +45" and -45" directions, and the remaining 10% in the 0" orientation. This gives the predominate stiffness in the spanwise direction for this relatively high aspect ratio wing. A total skin thickness of 0.2 inches at the wing midspan was chosen with the skin thickness tapering with the airfoil thickness
4. Airfoil OW 70-10-12