SUPERSONIC LATERAL-DIRECTIONAL STABILITY CHARACTERISTICS OF A 45° SWEPT WING-BODY-TAIL MODEL WITH VARIOUS BODY CROSS-SECTIONAL SHAPES

摘要

An investigation has been made in the Langley k- by 4-foot supersonic pressure tunnel to determine the lateral, directional, and longitudinal stability characteristics of a 45° swept wing-body-tail model having various body cross sectional shapes. The cross-sectional shapes tested include a circle, an ellipse, a flat-bottom teardrop, an upright triangle, and an inverted triangle. Tests were performed at angles of attack of about -4° to 22°, at angles of side slip from about -4° to 8°, at Mach numbers of 1.41 and 2.20, and at a Reynolds number per foot of 3-0 X 106.nThe results indicate that the directional stability, particularly for high angles of attack, was found to be dependent on body cross-sectional shape. A circular fuselage generally indicates the least effects of angle of attack on the lateral-directional stability characteristics of any of the body shapes tested.