SWEEPFORWARD IN CONJUNCTION WITH A FUSELAGE

Pressure distributions and wake measurements have been obtained for wings with 300 and 11.50 of sweepforward, in conjunction with a mid-wing fuselage, at Mach numbers to 0.96. The wings had an NACA 65-210 section, a taper ratio of 0.38, and aspect ratios of 7.5 and 5.2. A study of the results of these measurements indicates that severe nega-tive pressure-coefficient peaks develop on the leading edge of the upper surface of the sweptforward wings near the wing-fuselage juncture, even for low angles of attack at a Mach nuinber.of 0.60. As the angle of attack was increased, severe separation developed initially in this region. Shocks and associated separation occurred initially near the wing-fuselage juncture of the sweptforward wings at Mach numbers below the drag-divergence values. At Mach numbers above the drag-divergence values, the separation on this region of the wing with 300 of sweep-forward was more severe than that on the same wing with no sweep for the same Mach numbers and angles of attack. No loss in section normal-force coefficient was-associated with this separation. The separation, associated with the onset of shock on the upper surface of the mid-semispan and outboard regions of the wing with 300 of sweepforward, was considerably less severe than that on the corresponding regions of the same wing with 300 of sweepback at the same Mach numbers and angles of attack