Low speed wind tunnel investigation of high lift devices on a 65 degree swept-back supersonic wing of 3.44 aspect ratio

A low speed survey was conducted on a 3.44 aspect ratio wing having a 65° swept-back leading edge and double wedge symmetrical airfoil section to obtain information as to the effectiveness of various high-lift devices. These devices included trailing edge split and extended split flaps, leading edge split flaps, slats and combined configurations. Tests were carried out on the wing with and without the fuselage and horizontal tail surface. The split flaps increased the lift over the lower ranges of angle of attack only. The extended split flaps increased the lift over the whole angle of attack range. Hose flaps showed practically no gain over any of the range when used by themselves. However, when combined with the trailing edge split flaps in the wing-fuselage configuration, the optimum maximum lift conditions were obtained. Addition of the fuselage and horizontal tail surfaces each produced considerable increments of lift. In all configurations except leading edge flaps in the inboard position undesirably large negative pitching moments resulted. However, they had stabilizing tendencies except where there were irregularities in the lift curves.