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set_radius(self,
radial_position)
Set the radial position of the section along the blade radius |
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set_chord(self,
chord)
Set the chord of the section |
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set_twist(self,
value,
unit='deg')
Set the twist angle for the section according to the blade
plane. |
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_get_direct_coefficients(self,
time_step)
Return the lift and drag coefficient |
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_apply_dynamic_stall(self,
key,
attached_coeff,
separated_coeff,
time_step)
Apply the dynamic stall model |
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_get_dynamic_stall_coefficients(self,
time_step)
Return the lift and drag coefficients by applying a dynamic stall
model |
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init_unsteady(self)
Initialize the unsteady calculation |
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calculate_rvector(self)
Calculate the section vector |
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calculate_relative_velocity(self,
rotational_speed,
cone_angle,
pitch_matrix)
Calculate the relative velocity from the velocity triangle |
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calculate_pressures(self,
air_density,
time_step,
pitch)
Calculate the aerodynamics pressures (in N/m)
at the section |
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calculate_qs_induced_velocity(self,
prandlt_factor,
air_density,
nb_blades)
Calculate the quasi static induced velocity, without taking into
account the dynamic wake |
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disable_dynamic_wake(self,
induction_factor_max,
adjust_factor,
wind_speed,
time_step,
blade_radius)
Disable the dynamic wake by giving the reference of the quasi
static induced velocity to the current induced velocity |
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apply_dynamic_wake(self,
induction_factor_max,
adjust_factor,
wind_speed,
time_step,
blade_radius)
Calculate the current induced velocity by applying the two filters
of the dynamic wake |
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