EFFECT OF LEADING-EDGE SWEEPBACK ON LIFT, DRAG, AND PITCHING-MOMENT CHARACTERISTICS OF THIN WINGS OF ASPECT RATIO 3 AND TAPER RATIO 0.4 AT SUBSONIC AND SUPERSONIC SPEEDS

摘要

Wind-tunnel studies were conducted to determine the effect of leading-edge sweepback on the lift, drag, and pitching-moment characteristics of 3-percent-thick wings of aspect ratio 3 and taper ratio 0.4. Data for a wing with 45.0° sweepback, tested in combination with a high-fineness-ratio body, are presented for angles of attack from -6° to +17° at Mach numbers from 0.6l to 0.93 and 1.20 to 1.90 at Reynolds numbers of 2.5 and 3.8 million. Comparisons are made between these data and the results for wings with 19.1° and 53.1° sweepback reported in NACA RM's A53A30 and A54J20, respectively.nIncreasing the leading-edge sweepback of the wings decreased both the lift-curve slope and the variation of static longitudinal stability at zero lift with Mach number. In general, the drag coefficient at zero lift was decreased with increasing sweepback at supersonic speeds.