WIND-TUNNEL INVESTIGATION OF THE STATIC ANDnDYNAMIC-ROTARY STABILITY DERIVATIVES OFnA FLAT-TOP WING-BODY MODEL AT MACHnNUMBERS OF 2.5, 3.0, AND 3.5

摘要

The results of a wind-tunnel investigation of the static and dynamic-rotary stability derivatives for a flat-top wing-body model are presented. The test was conducted at Mach numbers of 2.5, 3.0, and 3.5, and a Reynolds number of 5 million. The angle-of-attack range was approximately -l6° to +12° at 0° sideslip. Also, static data were obtained through the angle-of-attack range at a constant 5° angle of sideslip and within an angle-of-sideslip range of -10° to +6° at a constant angle of attack of 6°.nThe model consisted of an arrow wing with tips drooped along a line inclined 3° to the model plane of symmetry, and a 3A-power ogive half body mounted beneath the wing. A ventral fin was located at the rear of the half body.