摘要: An investigation was conducted in the Langley 8-foot transonic pressure tunnel of a 1/9-scale model of an existing executive-type jet transport refitted with a supercritical wing. The supercritical wing had the same sweep as the o... 展开 An investigation was conducted in the Langley 8-foot transonic pressure tunnel of a 1/9-scale model of an existing executive-type jet transport refitted with a supercritical wing. The supercritical wing had the same sweep as the original airplane wing but had maximum thickness-chord ratios 33 percent larger at the mean geometric chord and almost 50 percent larger at the wing-fuselage juncture. Force and moment data are presented at Mach numbers from 0.25 to 0.90 at angles of attack that generally vary from -2 to 10 deg. Wing and fuselage pressure distributions are also presented for conditions near the cruise lift coefficient. 收起