Answer
See explanation
Work Step by Step
When supersonic flow impinges on a blunt body like the rounded nose of an aircraft, the wedge half-angle $\delta$ at the nose is $90^{\circ}$, and an attached oblique shock cannot exist, regardless of Mach number.
Therefore, a detached oblique shock must occur in front of all such blunt-nosed bodies, whether two-dimensional, axisymmetric, or fully threedimensional.
