1951•NASA STI Repository (National Aeronautics and Space Administration)Requires access
An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepforward in conjunction with a fuselage
R. T. Whitcomb
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Abstract
Report presenting pressure distributions, wake measurements, and tuft patterns for wings with 30 and 45 degrees of sweepback in conjunction with a midwing fuselage at Mach numbers to 0.96. The wings have an NACA 65-210 section, a taper ratio of 2.6:1, and aspect ratios of 7.5 and 5.2. The study indicated that when the Mach number reached high subsonic values at low angles of attack, the locations of peak negative pressure coefficients on the upper surfaces of the sections near the wing-fuselage junctures shifted rearward.