本文整理汇总了Python中SUAVE.Core.Data.drag_force_vector方法的典型用法代码示例。如果您正苦于以下问题：Python Data.drag_force_vector方法的具体用法？Python Data.drag_force_vector怎么用？Python Data.drag_force_vector使用的例子？那么, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类SUAVE.Core.Data的用法示例。
在下文中一共展示了Data.drag_force_vector方法的3个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的Python代码示例。
示例1: compute_forces
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import drag_force_vector [as 别名]
def compute_forces(self,conditions):
# unpack
q = conditions.freestream.dynamic_pressure
Sref = self.geometry.reference_area
#
CL = conditions.aerodynamics.lift_coefficient
CD = conditions.aerodynamics.drag_coefficient
N = q.shape[0]
L = np.zeros([N,3])
D = np.zeros([N,3])
L[:,2] = ( -CL * q * Sref )[:,0]
D[:,0] = ( -CD * q * Sref )[:,0]
results = Data()
results.lift_force_vector = L
results.drag_force_vector = D
return results
示例2: evaluate
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import drag_force_vector [as 别名]
def evaluate(self,conditions):
""" process vehicle to setup geometry, condititon and settings
Inputs:
conditions - DataDict() of aerodynamic conditions
Outputs:
CL - array of lift coefficients, same size as alpha
CD - array of drag coefficients, same size as alpha
Assumptions:
linear intperolation surrogate model on Mach, Angle of Attack
and Reynolds number
locations outside the surrogate's table are held to nearest data
no changes to initial geometry or settings
"""
# unpack
settings = self.settings
geometry = self.geometry
surrogates = self.surrogates
q = conditions.freestream.dynamic_pressure
AoA = conditions.aerodynamics.angle_of_attack
Sref = geometry.reference_area
wings_lift_model = surrogates.lift_coefficient
# inviscid lift of wings only
inviscid_wings_lift = wings_lift_model(AoA)
conditions.aerodynamics.lift_breakdown.inviscid_wings_lift = inviscid_wings_lift
# lift needs to compute first, updates data needed for drag
CL = compute_aircraft_lift(conditions,settings,geometry)
# drag computes second
CD = compute_aircraft_drag(conditions,settings,geometry)
# pack conditions
conditions.aerodynamics.lift_coefficient = CL
conditions.aerodynamics.drag_coefficient = CD
# pack results
results = Data()
results.lift_coefficient = CL
results.drag_coefficient = CD
N = q.shape[0]
L = np.zeros([N,3])
D = np.zeros([N,3])
L[:,2] = ( -CL * q * Sref )[:,0]
D[:,0] = ( -CD * q * Sref )[:,0]
results.lift_force_vector = L
results.drag_force_vector = D
return results示例3: compute_forces
# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import drag_force_vector [as 别名]
def compute_forces(self,conditions):
"""The default function to compute forces.
Assumptions:
None
Source:
N/A
Inputs:
conditions.freestream.
dynamic_pressure [Pa]
conditions.aerodynamics.
lift_coefficient [-]
drag_coefficient [-]
Outputs:
results.
lift_force_vector [N]
drag_force_vector [N]
Properties Used:
self.geometry.reference_area [m^2]
"""
# unpack
q = conditions.freestream.dynamic_pressure
Sref = self.geometry.reference_area
#
CL = conditions.aerodynamics.lift_coefficient
CD = conditions.aerodynamics.drag_coefficient
N = q.shape[0]
L = np.zeros([N,3])
D = np.zeros([N,3])
L[:,2] = ( -CL * q * Sref )[:,0]
D[:,0] = ( -CD * q * Sref )[:,0]
results = Data()
results.lift_force_vector = L
results.drag_force_vector = D
return results