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Rotating Detonation Engines (RDEs) promise higher thermodynamic efficiency than conventional combustors, but they deliver a strongly unsteady flow to the turbine downstream. The effect of these fluctuations on stator performance remains experimentally uncharacterised. The unsteady aerodynamics of supersonic turbine stator cascades subjected to fluctuating inlet conditions are studied in this research. A cold linear blow-down wind tunnel is commissioned to test the fully supersonic cascade, with purpose-designed unsteadiness generators installed upstream to impose inlet disturbances at prescribed frequencies and amplitudes, reproducing conditions representative of RDE operation. Inlet and outlet flow fields are characterised in both steady and unsteady regimes by means of slow and fast-response pressure probes and multi-hole probes, from which the aerodynamic performance parameters are derived. Schlieren visualisation is applied to qualify the shock pattern upstream of and within the blade channel. Unsteady CFD simulations are conducted to support the interpretation of the experimental findings. Aerodynamic loss is ultimately assessed as a function of the inlet disturbance frequency, quantifying the variation of performance associated with detonation-like inflow.