Transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2: analysis of pressure distribution of wing-fuselage configuration having a wing of 45 degrees sweptback, aspect ratio 4, t

Abstract

Report presenting a pressure-distribution investigation in the high-speed tunnel of a wing-fuselage configuration as part of an NACA research program to determine effects of wing geometry on aerodynamic characteristics and to explore the nature of flow over the configuration. Measurements were made on a fuselage and wing-fuselage combination for a range of Mach numbers. Results regarding accuracy, figures of pressure distributions, pressure distributions on the wing and fuselage, results at several angles of attack, section loading characteristics, normal-force characteristics, pitching-moment characteristics, pressure-drag characteristics, and fuselage skin-friction drag are provided.