AERODYNAMIC CHARACTERISTICS OF A WING WITH QUARTER-CHORD LINE SWEPT BACK 35°, ASPECT RATIO 6, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL SECTION TRANSONIC-BUMP METHOD

摘要

Aa part of an NACA transonic research program a series of wing—body combinations are being investigated in the Langley high-speed 7— by 10—foot tunnel over a Mach number range from 0.60 to l.l8 by utilizing the transonic-bump teat technique.nThis paper presents the results of the investigation of a wing alone and wing—fuselage combination employing a 35° sweptback wing with aspect ratio 6, taper ratio 0.6, and an NACA 65AOO6 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic—pressure characteristics in the region of a probable tail location were obtained for these configurations and are presented for a range of tall heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.