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BoundaryLayerInviscidCoupling.py
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197 lines (165 loc) · 12.1 KB
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import openmdao.api as om
import numpy as np
import TransitionalBoundaryLayer as transitionalboundarylayer
import Inviscid as inviscid
import ITVInterpolator as itvinterpolator
# Use stagnation point position to locate two boundary layers
# Do some kind of magic to account for lower boundary layer going against the surface direction
# Run 1 way coupled analysis (use inviscid velocity as edge velocity to drive boundary layers)
class GenerateBLNodes(om.ExplicitComponent):
def initialize(self):
self.options.declare('num_inviscid_nodes')
self.options.declare('num_upper_lam_nodes')
self.options.declare('num_upper_turb_nodes')
self.options.declare('num_lower_lam_nodes')
self.options.declare('num_lower_turb_nodes')
def setup(self):
num_inviscid_nodes = self.options['num_inviscid_nodes']
num_upper_lam_nodes = self.options['num_upper_lam_nodes']
num_upper_turb_nodes = self.options['num_upper_turb_nodes']
num_lower_lam_nodes = self.options['num_lower_lam_nodes']
num_lower_turb_nodes = self.options['num_lower_turb_nodes']
self.add_input('panel_lengths', shape=(num_inviscid_nodes,))
self.add_input('stagnation_point_position', 1)
self.add_input('upper_transition_length', 0.05)
self.add_input('lower_transition_length', 0.05)
self.add_output('upper_length')
self.add_output('lower_length')
self.add_output('upper_laminar_node_positions', shape=(num_upper_lam_nodes,))
self.add_output('upper_turbulent_node_positions', shape=(num_upper_turb_nodes,))
self.add_output('lower_laminar_node_positions', shape=(num_lower_lam_nodes,))
self.add_output('lower_turbulent_node_positions', shape=(num_lower_turb_nodes,))
self.declare_partials('*', '*')
def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
num_upper_lam_nodes = self.options['num_upper_lam_nodes']
num_upper_turb_nodes = self.options['num_upper_turb_nodes']
num_lower_lam_nodes = self.options['num_lower_lam_nodes']
num_lower_turb_nodes = self.options['num_lower_turb_nodes']
l = inputs['panel_lengths']
s0 = inputs['stagnation_point_position']
tru = inputs['upper_transition_length']
trl = inputs['lower_transition_length']
perimeter = np.sum(l)
outputs['upper_length'] = perimeter - s0
outputs['lower_length'] = s0
outputs['upper_laminar_node_positions'] = np.linspace(s0, s0+tru, num_upper_lam_nodes)
outputs['upper_turbulent_node_positions'] = np.linspace(s0+tru, perimeter, num_upper_turb_nodes)
outputs['lower_laminar_node_positions'] = np.linspace(trl, s0, num_lower_lam_nodes)
outputs['lower_turbulent_node_positions'] = np.linspace(0, trl, num_lower_turb_nodes)
class BoundaryLayerCoupling(om.Group):
def initialize(self):
self.options.declare('num_base_points')
self.options.declare('num_upper_lam_nodes')
self.options.declare('num_upper_turb_nodes')
self.options.declare('num_lower_lam_nodes')
self.options.declare('num_lower_turb_nodes')
def setup(self):
num_base_points = self.options['num_base_points']
num_inviscid_nodes = num_base_points-1
num_upper_lam_nodes = self.options['num_upper_lam_nodes']
num_upper_turb_nodes = self.options['num_upper_turb_nodes']
num_lower_lam_nodes = self.options['num_lower_lam_nodes']
num_lower_turb_nodes = self.options['num_lower_turb_nodes']
self.add_subsystem('InviscidSubsystem',
inviscid.InviscidGroup(num_points=num_base_points),
promotes_inputs=['aerofoil_ccw_coordinates', 'alpha'],
promotes_outputs=['external_tangential_velocities',
'pressure_coefficients',
'stagnation_point_position',
'panel_lengths'])
self.add_subsystem('GenerateBLNodes', GenerateBLNodes(num_inviscid_nodes=num_inviscid_nodes,
num_upper_lam_nodes=num_upper_lam_nodes, num_upper_turb_nodes=num_upper_turb_nodes,
num_lower_lam_nodes=num_lower_lam_nodes, num_lower_turb_nodes=num_lower_turb_nodes),
promotes_inputs=['panel_lengths',
'stagnation_point_position',
'upper_transition_length',
'lower_transition_length'],
promotes_outputs=['upper_length',
'lower_length',
'upper_laminar_node_positions',
'upper_turbulent_node_positions',
'lower_laminar_node_positions',
'lower_turbulent_node_positions'])
self.add_subsystem('ITVInterpolatorGroup',
itvinterpolator.ITVInterpolatorGroup(num_inviscid_nodes=num_inviscid_nodes,
num_upper_lam_nodes=num_upper_lam_nodes, num_upper_turb_nodes=num_upper_turb_nodes,
num_lower_lam_nodes=num_lower_lam_nodes, num_lower_turb_nodes=num_lower_turb_nodes),
promotes_inputs=['panel_lengths',
'external_tangential_velocities',
'upper_laminar_node_positions',
'upper_turbulent_node_positions',
'lower_laminar_node_positions',
'lower_turbulent_node_positions'],
promotes_outputs=['interpolated_external_tangential_velocities',
'lower_turbulent_external_tangential_velocities',
'lower_laminar_external_tangential_velocities',
'upper_laminar_external_tangential_velocities',
'upper_turbulent_external_tangential_velocities',
'viscous_node_positions',
'inviscid_node_positions'])
self.add_subsystem('InvertLowerLamVelocities', om.ExecComp('neg_lower_laminar_external_tangential_velocities = -lower_laminar_external_tangential_velocities[::-1]', lower_laminar_external_tangential_velocities=np.ones(num_lower_lam_nodes)),
promotes_inputs=['lower_laminar_external_tangential_velocities'],
promotes_outputs=['neg_lower_laminar_external_tangential_velocities'])
self.add_subsystem('InvertLowerTurbVelocities', om.ExecComp('neg_lower_turbulent_external_tangential_velocities = -lower_turbulent_external_tangential_velocities[::-1]', lower_turbulent_external_tangential_velocities=np.ones(num_lower_turb_nodes)),
promotes_inputs=['lower_turbulent_external_tangential_velocities'],
promotes_outputs=['neg_lower_turbulent_external_tangential_velocities'])
self.add_subsystem('UpperBoundaryLayer', transitionalboundarylayer.TransitionalBoundaryLayerGroup(num_lam_nodes=num_upper_lam_nodes, num_turb_nodes=num_upper_turb_nodes),
promotes_inputs=[('total_length', 'upper_length'),
('lam_node_external_tangential_velocities', 'upper_laminar_external_tangential_velocities'),
('turb_node_external_tangential_velocities', 'upper_turbulent_external_tangential_velocities'),
'kinematic_viscosity'],
promotes_outputs=[('lam_momentum_thickness', 'upper_lam_momentum_thickness'),
('turb_momentum_thickness', 'upper_turb_momentum_thickness'),
('lam_displacement_thickness', 'upper_lam_displacement_thickness'),
('turb_displacement_thickness', 'upper_turb_displacement_thickness'),
('lam_Cf', 'upper_lam_Cf'),
('turb_Cf', 'upper_turb_Cf'),
('transition_distance', 'upper_transition_length')])
self.add_subsystem('LowerBoundaryLayer', transitionalboundarylayer.TransitionalBoundaryLayerGroup(num_lam_nodes=num_lower_lam_nodes, num_turb_nodes=num_lower_turb_nodes),
promotes_inputs=[('total_length', 'lower_length'),
('lam_node_external_tangential_velocities', 'neg_lower_laminar_external_tangential_velocities'),
('turb_node_external_tangential_velocities', 'neg_lower_turbulent_external_tangential_velocities'),
'kinematic_viscosity'],
promotes_outputs=[('lam_momentum_thickness', 'lower_lam_momentum_thickness'),
('turb_momentum_thickness', 'lower_turb_momentum_thickness'),
('lam_displacement_thickness', 'lower_lam_displacement_thickness'),
('turb_displacement_thickness', 'lower_turb_displacement_thickness'),
('lam_Cf', 'lower_lam_Cf'),
('turb_Cf', 'lower_turb_Cf'),
('transition_distance', 'lower_transition_length')])
self.linear_solver = om.LinearRunOnce()
self.nonlinear_solver = om.NewtonSolver(solve_subsystems=True, maxiter=30, iprint=2)
if __name__ == "__main__":
import matplotlib.pyplot as plt
aerofoil_path = r"C:\Users\euana\Documents\Important Documents\Optimisation Project\TASWiG\aerofoils\NACA_64-012"
soln_path = r"C:\Users\euana\Documents\Important Documents\Optimisation Project\TASWiG\aerofoils\NACA_64-012_JF"
aerofoil = np.loadtxt(aerofoil_path).T
num_points = aerofoil.shape[1]
num_ul = 20
num_ut = 75
num_ll = 50
num_lt = 50
p = om.Problem(model=BoundaryLayerCoupling(num_base_points=num_points,
num_upper_lam_nodes=num_ul, num_upper_turb_nodes=num_ut,
num_lower_lam_nodes=num_ll, num_lower_turb_nodes=num_lt))
p.model.set_input_defaults('alpha', 3, units='deg')
p.model.set_input_defaults('aerofoil_ccw_coordinates', aerofoil)
p.model.set_input_defaults('kinematic_viscosity', 1.81e-5/10)
p.setup()
p.run_model()
node_positions = np.concatenate((p.get_val('upper_laminar_node_positions'), p.get_val('upper_turbulent_node_positions')))
Cf = np.concatenate((p.get_val('upper_lam_Cf'), p.get_val('upper_turb_Cf')))
d1 = np.concatenate((p.get_val('upper_lam_displacement_thickness'), p.get_val('upper_turb_displacement_thickness')))
d2 = np.concatenate((p.get_val('upper_lam_momentum_thickness'), p.get_val('upper_turb_momentum_thickness')))
fig, axs = plt.subplots(3, 1)
axs[0].plot(node_positions, d1, label='Displacement Thickness')
axs[0].set_title('Displacement Thickness')
axs[0].legend()
axs[1].plot(node_positions, d2, label='Momentum Thickness')
axs[1].set_title('Momentum Thickness')
axs[1].legend()
axs[2].plot(node_positions, Cf, label='Cf')
axs[2].set_title('Skin Friction Coefficient')
#axs[2].set_ylim(-0.0025, max(Cf))*2)
axs[2].legend()
plt.show()