Some compressibility effects on the lee side flow structures of cruciform wing-body configurations with very low aspect ratio wings

A series of validated numerical simulations of a tangent ogive circular body in combination with very low aspect ratio cruciform wings at supersonic Mach numbers and angles of attack up 25° have been performed. Inspection of the flow in the cross flow planes revealed that symmetric vortex shedding occurs when the cross flow velocity is supersonic not only in the accelerated flow region outside the vortices, but in particular, the reverse flow in the recirculation region. Symmetric vortex shedding occurs for tangent ogive bodies at cross flow Mach numbers greater than 0.65, and for circular bodies with cruciform wings in the '+' orientation and span to body diameter ratios of 1.25 at cross flow Mach numbers greater than 0.55.