Algebraic transitional extensions for the accurate computation of laminar separation bubbles are developed for use with k-ω models. The transitional model, based on integral boundary-layer parameters and transition criteria, introduces streamwise-variable weighting of the production terms in the k-ω equations and delay of the shear-stresslimiter activation. Calibration to fit available DNS data yields satisfactory results for a flat-plate reference case, both for skin-friction and velocity-profiles. It is shown that the model can be adapted to different k-ω variants by appropriate calibration of coefficients. The model is then validated for 2 airfoil test-cases, both for very low and higher Reynolds numbers, a NACA 0012 airfoil at chord-based Reynolds number Re c = 10 5 and angle-of-attack α = 10.55 deg and a S809 airfoil at Re c = 2 × 10 6 and α = 1 deg. For both application cases comparison with available data is satisfactory. Nomenclature c = airfoil chord length (m) C lim = shear-stress limiter delay function Cp = pressure coefficient