Low-Speed Investigation of the Effects of Large Wing-Sideslip Angles on the Aerodynamic Characteristics of Two Arrow-Wing-Fuselage Arrangements

A wind-tunnel investigation has been made of two methods proposed to reduce the high sinking speeds and improve the landing characteristics of low-aspect-ratio hypersonic airplanes by placing the wing at large angles of sideslip to increase its effective aspect ratio. The models investigated had conical fuselages and arrow wings, with a leading-edge sweep-back of 77.4deg, an aspect ratio of 1.23, and a 4-percent-thick straight-wedge section. For one model, the wing was pivoted on the fuselage to angles of wing sideslip from 0 to 90deg. For the other model, the wing was fixed to the fuselage, and the wing and fuselage were yawed together to sideslip angles from 0 to 90deg. The investigation was made in the Langley 300-MPH 7- by 10-foot tunnel for an angle-of-attack range from -8 to above 28deg. Longitudinal stability and control through the use of horizontal tails with elevators was studied on the pivoted-wing configuration. The roll control for both configurations was studied with deflection of the apex portion of the wing about an axis along the wing center line. The use of flaps with the wing at large sideslip angles was also investigated.