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A vortex-based tip/smearing correction for the actuator line

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Figure

Fig. 1 – here with a Lamb–Oseen vortex core model (Lamb,1932; Oseen, 1911). Without viscosity (inviscid) the veloci-ties approach infinity towards the vortex centre
Figure 3. Thrust sensitivity of the NREL 5-MW AL simulations at{a 8 ms−1 wind speed with respect to grid size, doubling the domainsize and halving the time step at two smearing length scales (Ns =9,19}, Tref = {4.20,4.06} × 105 N).
Figure 4. Trailed vorticity path. The blade rotates in the x−y planeand z points downstream
Figure 5. Definition of the wing test cases with either a rectangularor elliptic planform
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