Effects of Wing Leading-Edge Flap Deflections on Subsonic Longitudinal Aerodynamic Characteristics of a Wing-Fuselage Configuration With a 44° Swept Wing

摘要

An investigation has been conducted to determine the effects of wing leading-edge flap deflections on the subsonic longitudinal aerodynamic characteristics of a wing-fuselage configuration with a 44° swept wing. The tests were conducted at Mach numbers from O.4O to O.85, corresponding to Reynolds numbers (based on wing mean geometric chord) of 2.37×10° to 4.59 ×10 and at angles of attack from -3° to 22°. The configurations under study included a wing-fuselage configuration and a wing-fuselage-strake configuration. Each configuration had multisegmented, constant-chord leading-edge flaps which could be deflected independently or in various combinations.