SUBSONIC AND SUPERSONIC LONGITUDINAL STABILITY AND CONTROL CHARACTERISTICS OF AN AFT-TAIL FIGHTER CONFIGURATION WITH CAMBERED AND UNCAMBERED WINGS AND CAMBERED FUSELAGE

摘要

An investigation has been conducted over a Mach number range from 0.50 to 2.16 to determine the longitudinal aerodynamic characteristics of a fighter airplane con¬cept. The configuration incorporates a cambered fuselage with a single external-compression horizontal-ramp inlet, a clipped arrow wing, twin horizontal tails, and a single vertical tail. The wing camber surface was optimized in drag due to lift and was designed to be self-trimming at Mach 1.40 and at a lift coefficient of 0.20. The fuselage was cambered to preserve the design wing loadings on the part of the theoretical wing enclosed by the fuselage. An uncambered or flat wing of the same planform and thickness ratio distribution was also tested.