26TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES COMPARISON OF SHOCK WAVE INTERACTION FOR THE THREE-DIMENSIONAL SUPERSONIC BIPLANE WITH DIFFERENT PLANAR SHAPES

The supersonic biplane is well known for the airfoil which has zero wave drag at the supersonic speed. However a Mach cone is generated at the wing tip and disturbs the shock wave interaction of the rectangular supersonic biplane with finite span length. The drag increases near the wing tip due to this disturbance. By devising its planar shape, the effect of the wing-tip can be reduced. This paper investigates on the phenomenon of the three-dimensional shock wave interaction for the three-dimensional supersonic biplane with four different kinds of planar shapes using Computational Fluid Dynamics. The drag becomes small when the wing has a small taper ratio, but excessive taper can also lead to more drag than the rectangular wing. When the wing has small sweepback angle and adequate taper ratio, its wing section has better shock wave interaction than that of the two-dimensional supersonic biplane