this paper, a preliminary performance assessment of the coupling between a wide-speed-range helicopter rotor and the connected turboshaft engine was carried out. For this purpose, a well-known test case has been chosen (UH-60A helicopter equipped with a GE-T700 engine) to study the implications of such coupling from both the helicopter and theengineviewpoints.Asimple helicopterrotorcalculationmodelisusedtodeterminetheoptimumrotorspeedand required rotor power in various flight conditions. Next, these data are used for the engine-performance analysis, which was carried out using a zero-dimensional, block-based validated engine model to determine the fuel weight necessary to accomplish a given simple mission (i.e., to fly in trimmed forward flight for a given time). The results obtained are compared with the baseline helicopter/engine configuration, and the implications of using variablespeed technology are clearly highlighted.