Abstract
The main results from a recently developed vortex model are implemented into a Blade Element Momentum(BEM) code. This implementation accounts for the effect of finite tip-speed ratio, an effect which was not considered in standard BEM yaw-models. The model and its implementation are presented. Data from the MEXICO experiment are used as a basis for validation. Three tools using the same 2D airfoil coefficient data are compared: a BEM code, an Actuator-Line and a vortex code. The vortex code is further used to validate the results from the newly implemented BEM yaw-model. Significant improvements are obtained for the prediction of loads and induced velocities. Further relaxation of the main assumptions of the model are briefly presented and discussed.
Highlights
The analytical studies from Glauert in 1926 [1] and Coleman in 1945 [2] form the basis of most yaw-models implemented in Blade Element Momentum(BEM) codes
The ratio between the right cylinder induction and the skewed cylinder induction provides a correction factor that is applied in BEM codes
Three tools using the same 2D airfoil coefficient data were used in this study
Summary
The analytical studies from Glauert in 1926 [1] and Coleman in 1945 [2] form the basis of most yaw-models implemented in Blade Element Momentum(BEM) codes These models strictly apply to rotors of infinite tip-speed ratios. Coleman focused on the axial velocity induced by the tangential vorticity component which is the main source of induction for large tip-speed ratios. To implement BEM yaw-models based on vortex theory results it will be assumed that the differences in induced velocities between the right and skewed vortex systems reflects the change of induced velocities that should apply to correct momentum theory from the right case to the skewed case. It is first chosen to use a single vortex cylinder representative of the rotor This is the option chosen when using Coleman or Glauert yaw-models.
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