def __defaults__(self):
self.training = Data()
self.training.angle_of_attack = np.array([-10.,0.,10.]) * Units.deg
self.training.lift_coefficient = None
self.training.drag_coefficient = None
self.training.pitch_moment_coefficient = None
self.surrogates = Data()
self.surrogates.lift_coefficient = None
self.surrogates.induced_drag_coefficient = None
self.surrogates.pitch_moment_coefficient = None
self.avl_callable = AVL_Callable()
self.avl_callable.keep_files = False
self.avl_callable.settings.filenames.run_folder = 'avl_surrogate_files'
self.geometry = None
self.finalized = False
return
def __defaults__(self):
self.training = Data()
self.training.angle_of_attack = np.array([-10., 0., 10.]) * Units.deg
self.training.lift_coefficient = None
self.training.drag_coefficient = None
self.training.pitch_moment_coefficient = None
self.surrogates = Data()
self.surrogates.lift_coefficient = None
self.surrogates.induced_drag_coefficient = None
self.surrogates.pitch_moment_coefficient = None
self.avl_callable = AVL_Callable()
self.avl_callable.keep_files = False
self.avl_callable.settings.filenames.run_folder = 'avl_surrogate_files'
self.geometry = None
self.finalized = False
return
class AVL(Aerodynamics,Surrogate):
''' This class only builds and evaluates an avl surrogate of aerodynamics
It must be patched into a markup analysis if more fidelity is needed.
The surrogate models lift coefficient, induced drag coefficient, and
pitching moment coefficient versus angle of attack.
'''
def __defaults__(self):
self.training = Data()
self.training.angle_of_attack = np.array([-10.,0.,10.]) * Units.deg
self.training.lift_coefficient = None
self.training.drag_coefficient = None
self.training.pitch_moment_coefficient = None
self.surrogates = Data()
self.surrogates.lift_coefficient = None
self.surrogates.induced_drag_coefficient = None
self.surrogates.pitch_moment_coefficient = None
self.avl_callable = AVL_Callable()
self.avl_callable.keep_files = False
self.avl_callable.settings.filenames.run_folder = 'avl_surrogate_files'
self.geometry = None
self.finalized = False
return
def finalize(self):
if not self.finalized:
print 'Building AVL Surrogate'
self.avl_callable.features = self.geometry
self.avl_callable.finalize()
self.sample_training()
self.build_surrogate()
self.finalized = True
print 'Done'
return
initialize = finalize
def sample_training(self):
# define conditions for run cases
run_conditions = Aero_Conditions()
ones_1col = run_conditions.ones_row(1)
run_conditions.weights.total_mass = ones_1col*self.geometry.mass_properties.max_takeoff
run_conditions.freestream.mach_number = ones_1col * 0.0
run_conditions.freestream.velocity = ones_1col * 150 * Units.knots
run_conditions.freestream.density = ones_1col * 1.225
run_conditions.freestream.gravity = ones_1col * 9.81
# set up run cases
alphas_1d = self.training.angle_of_attack
alphas = alphas_1d.reshape([alphas_1d.shape[0],1])
run_conditions.expand_rows(alphas.shape[0])
run_conditions.aerodynamics.angle_of_attack = alphas
# run avl
results = self.avl_callable.evaluate_conditions(run_conditions)
self.training.lift_coefficient = results.aerodynamics.lift_coefficient.reshape(alphas_1d.shape)
self.training.induced_drag_coefficient = \
results.aerodynamics.drag_breakdown.induced.total.reshape(alphas_1d.shape)
self.training.pitch_moment_coefficient = \
results.aerodynamics.pitch_moment_coefficient.reshape(alphas_1d.shape)
return
def build_surrogate(self):
# unpack
training_data = self.training
AoA_data = training_data.angle_of_attack
CL_data = training_data.lift_coefficient
CDi_data = training_data.induced_drag_coefficient
Cm_data = training_data.pitch_moment_coefficient
# pack for surrogate
X_data = np.reshape(AoA_data,-1)
# assign models
lift_model = np.poly1d(np.polyfit(X_data,CL_data,1))
drag_model = np.poly1d(np.polyfit(X_data,CDi_data,2))
pitch_model = np.poly1d(np.polyfit(X_data,Cm_data,1))
# populate surrogates
self.surrogates.lift_coefficient = lift_model
self.surrogates.induced_drag_coefficient = drag_model
self.surrogates.pitch_moment_coefficient = pitch_model
return
def evaluate(self,state,settings=None,geometry=None):
# unpack
aoa = state.conditions.aerodynamics.angle_of_attack
Sref = self.geometry.reference_area
# evaluate surrogates
CL = self.surrogates.lift_coefficient(aoa)
CDi = self.surrogates.induced_drag_coefficient(aoa)
Cm = self.surrogates.pitch_moment_coefficient(aoa)
# pack conditions
state.conditions.aerodynamics.lift_coefficient = CL
state.conditions.aerodynamics.drag_coefficient = CDi
state.conditions.aerodynamics.pitch_moment_coefficient = Cm
# pack results
results = Data()
results.lift_coefficient = CL
results.drag_coefficient = CDi
results.induced_drag_coefficient = CDi
results.pitch_moment_coefficient = Cm
#results.update( self.compute_forces(state.conditions) )
return results
def evaluate_lift(self,state):
# unpack
aoa = state.conditions.aerodynamics.freestream.angle_of_attack
Sref = self.geometry.reference_area
# evaluate surrogates
CL = self.surrogates.lift_coefficient(aoa)
# pack conditions
state.conditions.aerodynamics.lift_coefficient = CL
# pack results
results = Data()
results.lift_coefficient = CL
return results
class AVL(Aerodynamics, Surrogate):
''' This class only builds and evaluates an avl surrogate of aerodynamics
It must be patched into a markup analysis if more fidelity is needed.
The surrogate models lift coefficient, induced drag coefficient, and
pitching moment coefficient versus angle of attack.
'''
def __defaults__(self):
self.training = Data()
self.training.angle_of_attack = np.array([-10., 0., 10.]) * Units.deg
self.training.lift_coefficient = None
self.training.drag_coefficient = None
self.training.pitch_moment_coefficient = None
self.surrogates = Data()
self.surrogates.lift_coefficient = None
self.surrogates.induced_drag_coefficient = None
self.surrogates.pitch_moment_coefficient = None
self.avl_callable = AVL_Callable()
self.avl_callable.keep_files = False
self.avl_callable.settings.filenames.run_folder = 'avl_surrogate_files'
self.geometry = None
self.finalized = False
return
def finalize(self):
if not self.finalized:
print 'Building AVL Surrogate'
self.avl_callable.features = self.geometry
self.avl_callable.finalize()
self.sample_training()
self.build_surrogate()
self.finalized = True
print 'Done'
return
initialize = finalize
def sample_training(self):
# define conditions for run cases
run_conditions = Aero_Conditions()
ones_1col = run_conditions.ones_row(1)
run_conditions.weights.total_mass = ones_1col * self.geometry.mass_properties.max_takeoff
run_conditions.freestream.mach_number = ones_1col * 0.0
run_conditions.freestream.velocity = ones_1col * 150 * Units.knots
run_conditions.freestream.density = ones_1col * 1.225
run_conditions.freestream.gravity = ones_1col * 9.81
# set up run cases
alphas_1d = self.training.angle_of_attack
alphas = alphas_1d.reshape([alphas_1d.shape[0], 1])
run_conditions.expand_rows(alphas.shape[0])
run_conditions.aerodynamics.angle_of_attack = alphas
# run avl
results = self.avl_callable.evaluate_conditions(run_conditions)
self.training.lift_coefficient = results.aerodynamics.lift_coefficient.reshape(
alphas_1d.shape)
self.training.induced_drag_coefficient = \
results.aerodynamics.drag_breakdown.induced.total.reshape(alphas_1d.shape)
self.training.pitch_moment_coefficient = \
results.aerodynamics.pitch_moment_coefficient.reshape(alphas_1d.shape)
return
def build_surrogate(self):
# unpack
training_data = self.training
AoA_data = training_data.angle_of_attack
CL_data = training_data.lift_coefficient
CDi_data = training_data.induced_drag_coefficient
Cm_data = training_data.pitch_moment_coefficient
# pack for surrogate
X_data = np.reshape(AoA_data, -1)
# assign models
lift_model = np.poly1d(np.polyfit(X_data, CL_data, 1))
drag_model = np.poly1d(np.polyfit(X_data, CDi_data, 2))
pitch_model = np.poly1d(np.polyfit(X_data, Cm_data, 1))
# populate surrogates
self.surrogates.lift_coefficient = lift_model
self.surrogates.induced_drag_coefficient = drag_model
self.surrogates.pitch_moment_coefficient = pitch_model
return
def evaluate(self, state, settings=None, geometry=None):
# unpack
aoa = state.conditions.aerodynamics.angle_of_attack
Sref = self.geometry.reference_area
# evaluate surrogates
CL = self.surrogates.lift_coefficient(aoa)
CDi = self.surrogates.induced_drag_coefficient(aoa)
Cm = self.surrogates.pitch_moment_coefficient(aoa)
# pack conditions
state.conditions.aerodynamics.lift_coefficient = CL
state.conditions.aerodynamics.drag_coefficient = CDi
state.conditions.aerodynamics.pitch_moment_coefficient = Cm
# pack results
results = Data()
results.lift_coefficient = CL
results.drag_coefficient = CDi
results.induced_drag_coefficient = CDi
results.pitch_moment_coefficient = Cm
#results.update( self.compute_forces(state.conditions) )
return results
def evaluate_lift(self, state):
# unpack
aoa = state.conditions.aerodynamics.freestream.angle_of_attack
Sref = self.geometry.reference_area
# evaluate surrogates
CL = self.surrogates.lift_coefficient(aoa)
# pack conditions
state.conditions.aerodynamics.lift_coefficient = CL
# pack results
results = Data()
results.lift_coefficient = CL
return results