Abstract:
The tests were made in the 8 ft x 8 ft wind tunnel at R.A.E. Bedford on a 1/36 scale model of a possible design for a supersonic transport aircraft. The wing camber was designed, using slender-wing theory, to have attached flow at a CL of 0.02, and a shift forward of the centre of pressure, relative to the uncambered wing, of 0.3 c at CL = 0.1. The present investigation was restricted to determining the effects of the fm and nacelles on the longitudinal stability, drag, and lateral stability of the wing and to measurements of effectiveness, drag, and hinge moment of the controls.
