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An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
The lateral flow characteristics in the region of a vertical tail have been investigated experimentally and theoretically at low subsonic speeds. The effects of changes in wing-body geometry such as nose position and shape, fuselage cross-sectional shape, and wing vertical position are described. The theoretical model which approximates the separated flow phenomena by a simple cylinder-vortex flow is described in an appendix.