SUBSONIC WIND-TUNNEL INVESTIGATION OF THE EFFECT OF FUSELAGE AFTERBODY ON DIRECTIONAL STABILITY OF WING-FUSELAGE COMBINATIONS AT HIGH ANGLES OF ATTACK

摘要

A wind-tunnel study of the directional stability characteristics at high angles of attack of two wing-fuselage combinations has been conducted at subsonic speeds. The wings utilized were a 4—percent-thick unswept wing of aspect ratio 3.0 and a 6-percent-thick 45° sweptback wing of aspect ratio 4. The results indicated very large differences in the directional stability between the two wing-fuselage configurations at high angles of attack. The unswept-wing—fuselage combination became stable at high angles, whereas the sweptback-wing—fuselage combination became increasingly unstable. Tests with the fuselage afterbody removed indicated that these effects were associated with wing induced sidewash over the fuselage afterbody.