The HART II test of 2001 provided a significant and comprehensive database of rotor loads, blade motion, blade pressure distribution, acoustic signature and flow field data. A sub-set of these were released for public access worldwide and an International HART II Workshop was established in 2005. This Workshop, open to the international rotorcraft community, has been held since then at both the AHS Annual Forum as well as the European Rotorcraft Forum. Following the requests of participants, the HART II International Workshop database has been undergoing continuous development. This paper describes the current content and status of the data and the documentation material provided within the workshop database.

Retreating side helicopter blades often experience stall when flying at high speeds or at high thrusts. There are a number of consequences to stall which result in significant increases in blade stresses, vibration levels, pitch link loads and required shaft power. No real confidence exists today for the prediction of these effects on actual helicopter rotors since the models used in existing aeroelastic codes have usually been elaborated from simple 2D wind tunnel tests. A GARTEUR Action Group (Group for Aeronautical Research and Technology in EURope) has been assembled to evaluate the capabilities of the up‐to‐date dynamic stall models used in Europe for the prediction of rotor behavior in presence of stall, the work of which is reported here. Seven different stall models are described and then fitted to reproduce experimental 2D hysteresis loops. A series of calculations is then carried out for a flight condition with a high load factor. The unsteady stall models used are finally evaluated against detailed measurements on a model rotor in a wind tunnel. Conclusions are drawn relative to the state‐of‐the‐art of dynamic stall models, blade torsion and of rotor calculations in general.