2016
DOI: 10.1088/1742-6596/753/9/092001
|View full text |Cite
|
Sign up to set email alerts
|

Wind tunnel validation of AeroDyn within LIFES50+ project: imposed Surge and Pitch tests

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
2
1
1
1

Citation Types

1
31
0

Year Published

2017
2017
2022
2022

Publication Types

Select...
5
2

Relationship

1
6

Authors

Journals

citations
Cited by 41 publications
(36 citation statements)
references
References 5 publications
1
31
0
Order By: Relevance
“…The relative velocity at the hub is then equal to U rel = U ∞ + U dyn . The thrust variation is plotted as a function of the dynamic velocity at the hub following the methodology used by Bayati et al In this representation of the oscillating thrust Δ Thrust = f ( U dyn ), the slope of the elliptic curve corresponds to the aerodynamic damping, in‐phase with the velocity, whereas the hysteresis area is correlated with quadrature‐phase phenomena, which are aerodynamic added mass and stiffness. However, the differences between mean loadings in the three different models cannot be represented following this methodology as only the dynamic loadings are plotted.…”
Section: Resultsmentioning
confidence: 99%
“…The relative velocity at the hub is then equal to U rel = U ∞ + U dyn . The thrust variation is plotted as a function of the dynamic velocity at the hub following the methodology used by Bayati et al In this representation of the oscillating thrust Δ Thrust = f ( U dyn ), the slope of the elliptic curve corresponds to the aerodynamic damping, in‐phase with the velocity, whereas the hysteresis area is correlated with quadrature‐phase phenomena, which are aerodynamic added mass and stiffness. However, the differences between mean loadings in the three different models cannot be represented following this methodology as only the dynamic loadings are plotted.…”
Section: Resultsmentioning
confidence: 99%
“…As presented previously, the thrust oscillation at the motion frequency is extracted through a Fourier analysis. This thrust variation is then plotted as a function of the dynamic velocity at the equator of the VAWT (mid‐height of the rotor) following the methodology presented in Bayati et al on an HAWT. In this representation of the oscillating thrust Δ Thrust = f( U dyn ), the slope of the elliptic curve corresponds to the aerodynamic damping, in‐phase with the velocity whereas the hysteresis area is correlated with quadrature‐phase phenomena, which are aerodynamic added mass and stiffness.…”
Section: Resultsmentioning
confidence: 99%
“…This is done in order to ensure that the unsteady behaviour of the turbine is well reproduced by the model since the turbine is also going to be tested for unsteady condition (Bayati et al, 2016a). Moreover, it is reasonable to consider that, by first approximation, the unsteady behaviour of an aerodynamic body function of the first derivatives of the drag and lift curves calculated around the steady angle of attack (Cheli and Diana, 2015).…”
Section: Aerodynamic Designmentioning
confidence: 99%
“…Beside the steady aerodynamic curves, wind tunnel tests allowed for a first analysis of the unsteady scaled model response (Bayati et al, 2016a). As stated in Sec.4.1, the aerodynamic design of the scaled blade was done comparing the lift coefficient derivatives of the full scale and the model scale airfoil, this should ensure that the unsteady response of the scaled turbine due to dynamic variation of the operational parameters is similar to the DTU 10 MW one.…”
Section: Wind Tunnel Testsmentioning
confidence: 99%