Abstract:
Wind tunnel tests have been made at M = 2 on a 75° swept delta wing
in order to study the progressive breakdown of the leading edge vortices,
which occurs at high incidence. The incidence at which vortex breakdown
occurred at supersonic speeds was somewhat less than at low speeds, but
the pattern of breakdown appeared to be similar, although the spiralling
region of flow is much larger at supersonic speeds.
Quite slender objects placed downstream of the wing had appreciable
upstream effects, causing vortex breakdown to move upstream by as much as
20% of the root chord for the same incidence.
