This work presents the correlation of simulation results and flight test data for a high-speed (V = 220 kts), high advance ratio (μ > 0.5) flight of the compound helicopter X~3. The simulation tool chain consists of state-of-the-art coupling between the computational fluid dynamics (CFD) code FLOWer and the comprehensive analysis (CA) tool HOST. By applying a free-flight trim procedure, the experimental flight state is accurately represented in the simulation. The deviations of most trim controls is below 1° and the maximum deviation is less than 1.4°. The analysis of the high fidelity CFD results illustrates key features of the flow physics at this high advance ratio, such as wake interactions, reverse flow and advancing side loading. The correlation of rotor dynamics data between simulation and flight test is favorable. Good accordance is demonstrated for flap bending moments, torsion moments and pitch link loads. In contrast, the correlation is weaker for the chord bending moments for which it is shown that the interbladc damper and drive train model mostly determine the structural loads.
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