Large-scale tests have been made of a semispan model of a 60° sweptback wing-fuselage combination. The model was equipped with 25-percentchord, 36-percent-span, double-slotted flaps; 25-percent-chord, 43-percent-span ailerons; and 17.5-pereent-chord leading-edge slats having spans from 71 to 31 percent of the wing span. The wing had an aspect ratio of 3.5, taper ratio of 0.45, and NACA 64A010 airfoil sections normal to the wing 0.25-chord line. Additional tests were made with the double-slotted flap replaced by a split flap of identical chord and span. Most of the investigation was performed at a Reynolds number of 8.0 x 10. However, some force data are presented for a range of Reynolds numbers from 4.0 X 106 to 10.0 X 106.
展开▼
