GUST-TUNNEL INVESTIGATION TO DETERMINE EFFECTS OF CENTER-OF-GRAVITY POSITION ON THE GUST LOADS OF A DELTA-WING MODEL WITH LEADING EDGE SWEPT BACK 60°

摘要

A gust-tunnel investigation to determine the effects of center-of-gravity position on the gust loads of a delta-wing model with the leading edge swept back 60° was made over a range of center-of-gravity positions from 4 percent ahead of to 11 percent behind the leading edge of the mean geometric chord. This investigation indicated that a 1-percent rearward movement of the center-of-gravity position increased the acceleration increment in the sharp-edge gust by 0.5 percent. In a gust with a gradi¬ent distance of 6.5 chords, the acceleration increment was increased by approximately 2 percent for the same movement of the center of gravity. Comparison of these results with those for a conventional airplane model indicates that the change in load for both configurations would be nearly the same in a sharp-edge gust, but in a gust with a gradient distance of 6.5 chords, the change in load for a given change in center-of-gravity position would be approximately twice as great for the delta-wing model as for the conventional airplane model.