Airfoil models in the actuator line code assessed with near-wake measurements on a yawed rotor

摘要

The rotor aerodynamics codes that are embedded in an aero-elastic design tool employ coupled blade and wake aerodynamics models. It is concluded from recent comparisons of rotor aerodynamics modeling results with measurements that the blade model represents a major source of modeling uncertainty. The current research intends to assess the un?certainty of the 0ye and Beddoes-Leishman dynamic stall blade models implemented in a rotor aerodynamics code by comparison with wind tunnel measurements on a model rotor subject to yawed flow conditions. To focus on the uncertainty of the blade model, the wake modeling contribution to the overall modeling uncertainty should be reduced. The actuator line method is therefore selected as it consists of a coupled wake and blade model, where the wake is governed by the incompressible Reynolds Averaged Navier-Stokes equations; unsteady, asymmetric wakes can be modeled without violating model assumptions. For yawed flow conditions without dynamic stall, the unsteady spanwise a- and ^-distributions predicted by the actuator line method with the two blade models are similar. Furthermore, reasonable agreement is found between the model predictions and the measurements. For yawed flow conditions with dynamic stall, actuator line results obtained with the Beddoes-Leishman dynamic stall model agree best with experimentally observed flow separation regions.