Abstract:
The wings are of delta planform, with aspect ratio of exposed pairs of panels 0.31, and total span of 2.5 times the diameter of the body, which is of fineness ratio 19. The rectangular controls, of span equal to that of the wings, and the chord 0.5 times the body diameter, are mounted with a half chord gap to the wing trailing edge. Loads are measured on one control in addition to overall loads. The tests cover an incidence range up to 22 degrees for 0 and 45 degrees roll and a complete roll range for incidences of 6, 12 and 20 degrees with elevator angles of 0, 10, 20 and 30 degrees. A brief survey of the flow in the region of the tail at M = 2.8 at an incidence of 20 degrees is included. The results show that there are large variations with roll angle in both stabiliser effectiveness in pitch and elevator effectiveness. Aileron effectiveness is fairly constant. The rolling moment variation with roll angle on the complete model changes from being stable when one pair of wings is horizontal for all incidences at subsonic speeds and for low incidence at supersonic speeds, to being unstable for high incidence at supersonic speed. It is suggested that this effect may arise mainly from the interaction of the body vortices and of the vortices from the near horizontal wings with the wing on the leeside of the body.
