"my" airplane also has slats, so for example according to
NACA Report 732 I would expect it to have by far the highest velocity at the slat, not at the flap. Especially as the A340 uses single slotted and significantly less deflected fowler flaps than some of the Boeing aircraft.
Does anybody know another source of pressure/velocity distribution around a modern supercritical airfoil with slats ?
Edit: found another source,
AIAA 2002-0844, also confirming the lowest pressure / highest velocity at the fixed leading edge just aft of the slat and on the slat itself.