The instrumentation layout (see Fig. 1) shows the coordinates; Sta is the area on wing from station y = 180 in. to tip. The variation in SZ and MX with Mach number are shown in Figs. 2 and 3, respectively. Notice that the computed terms SZ and MX do not directly reflect the influence of drag force on the wing; however, the inclusion of drag terms in the assumed force distribution is necessary to account for drag effects on structural strain as recorded by the strain gauges. In addition to lift and drag distributions, an assumed twisting moment along the leading edge might be used to account for leading-edge suction effects. It was not used in this study.