Abstract:
Supersonic wind tunnel tests were made over an incidence range from -4 to +30 degrees for a range of roll angles on a scrims of conical slender delta wing and body combinations with a short afterbody on which a rectangular tail control surface is mounted. An examination is made of the characteristics of the wing and body combination and the approximate contributions of the individual Wing panels are deduced. The effectiveness of the tail control surfaces as stabilisers and as controls is examined for three different sizes of gap between the control and the wing trailing edge. The non linear behaviour of the oontrols tested is attributed at low incidences to the viscous losses due to the wing wake, and at high incidence to the influenoe of the expansion field from the wing trailing edge.
