Slotted, natural-laminar-flow airfoils can produce high lift coefficients with low sectional drag. This is done by using favorable pressure gradients to maintain laminar flow on the fore element and using the aft element for the pressure recovery. However, the configuration creates a concave region at the rear of the fore element that is susceptible to Goertler instabilities. This work seeks to investigate and characterize the growth of Goertler instabilities on slotted, natural-laminar-flow airfoils. Three airfoils are considered: the S414.LSLTT, S103, and S207. Goertler transition is predicted to be unlikely on the S414.LSLTT, but likely on the S103 and S207. Reynolds number is also seen to have a significant influence on estimates of the S103 amplification ratios. The effects of Goertler transition on the S207 are also briefly discussed, including a notable drag increase.