Separated Flow Around a Delta Wing in Combination with a Body

Summary

The spatial flows in the lee side of a delta wing in supersonic flow are characterized by formation of a complex votex structure and the origin of internal shock waves. The latter under definite conditions also lead to formation of local separation zones and vortices. In combination with a body, the flow around such a wing is accompanied by interaction of the body vortices with those of the wing leading to the change of the integral characteristics of the configuration. The present paper is devoted to the study of the body influence peculiarities on the flow around the wing. The delta wing of diamond-shaped profile with sharp leading and trailing edges is the subject under study. Geometrical characteristics of the wing are the span-chord ratio λ = 1.41, the sweep angle along the leading edge χ = 70°40′, the maximal relative thickness$\overline C$ = 3,3%. The model construction permitted one to mount the wing in the position of a midwing in different places of the cylindrical part of the body in such a way that the length of the stern part could change from the maximal up to the complete absence. Experiments were carried out in supersonic wind tunnel T-313 of the Institute of Theoretical and Applied Mechanics of the Siberian Division of the USSR Academy of Sciences at the free stream velocities M_∞ = 2 (subsonic leading edge of the wing) and M_∞ = 4 (supersonic leading edge). The angles of attack of models changed within the limits α = 0°–21°. The corresponding Reynolds numbers calculated per 1 m accounted for Re = (24 and 56) · 10⁶m⁻1.