Stalling means that flow separation increases so lift does no longer grow with angle of attack. This flow separation happens mostly over the rear, inner part of the wing, where the local surface inclination has a backward component.
Now compare the pressure over an airfoil for fully attached and partially separated flow, just as it looks near or at stall. The plot below shows an XFOIL result for an airfoil at 12° angle of attack. The dashed lines show the inviscid pressure distribution (the one without separation) while the solid lines show the viscous pressure distribution with separated flow over the last 20% of the upper side. If you need more information to interpret the plot, please consult this and this answer.
Note that the scale on the y axis is negative: A more negative value means more suction. The stalling airfoil shows lower suction over most of the chord and only over the last 10% its local pressure is lower than it would be without separation.
This means that stall reduces suction over the area of the wing which points forward (there is really the expression nose or leading edge thrust for this suction) while it increases suction over the part that points most backward. In sum, both effects increase drag.
Is this an increase in induced drag or parasitic drag?
Actually, it is a lift deficit due to flow separation while induced drag still grows. Near stall more lift has to be bought by a disproportionate increase in angle of attack which brings with it an equally disproportionate increase in both induced and parasitic drag. Post-stall, lift drops again but drag continues to rise.