<p>Utilizing highly loaded blades in low-pressure turbine component of modern turbofan engines is attractive among gas turbine designers, because it is associated with considerable effects on maximizing engine thrust-to-weight ratio and reduction of fuel consumption. Hence, development of knowledge on aerodynamics of this type of blades would be crucial. In the present research work, initially, effects of Reynolds number and freestream turbulence intensity (FSTI) on steady aerodynamic of a linear cascade of high-lift turbine blades are studied, experimentally and numerically. Reynolds number and FSTI have been ranged between 1.2 and 3.52 × 10⁵ and 1.4 and 3.7%, respectively, which are consistent with high-lift turbine blades under typical cruise conditions of aircraft. Then, unsteady performance of the blades was investigated under various frequencies of upstream wake flows, produced by a suitable wake generator apparatus. Distributions of pressure and skin friction coefficients, intermittency factor, and velocity profiles provided to identify flow separation, commencement of transition, and possible re-attachment positions of the separated flow. Results showed that increasing the Reynolds number at a constant FSTI, or vice versa, causes the total pressure loss and total drag to decrease and the lift force to increase. The reason behind these advantages is strongly related to impingement of the upstream wakes to the blade surface. This event delays flow separation and accelerates commencement of transition on the blade surfaces. Unsteady results showed that variable kinematics of wake flow in a transient interval during its convection through the blade passage leads to increasing of local velocities on the blade suction surface. This in turn causes the blade lift force and also the outlet dynamic pressure of flow passage to increase.</p>