Aircraft with Flying wing configuration, such as the B2 bomber, fly at high subsonic speeds. During such a case, the airflow is at a high subsonic speed at the leading edge, and accerelates through to supersonic speeds as it moves over the front - upper portion of the wing surface. As the wing profile (chord wise) changes to converge towards the trailing edge, the airflow attempts to decelerate from supersonic to subsonic speeds. However, this transition is only possible through a chordwise oblique shock wave. Now, this oblique shocks profile will look like the blue line in your diagram above, but will be sitting at some near-mid chord position.
If the flying wing body is increases speed towards sonic velocity of the air, then this chord wise transition shock wave will become stronger and move just in front of the body leading edge. Finally, once the body is moving at supersonic speeds, the transition shock will become a bow shock in front of the leading edge. In addition to this, there will also be two termination shock waves sitting at the leading edge, one for the upper surface airflow and the other for the lower.
The angle of the shock wave profile will be greatest at low supersonic speeds, but beyond the bow stick sitting in front of the leading edge will narrow in angle and so will its spanwise angle. At hypersonic speeds, the distance between the front shock and leading edge will reduce, leading to immense heat energy being impinged onto the body.
Hope this helps