# RCAIDE/Library/Methods/Aerodynamics/Athena_Vortex_Lattice/build_VLM_surrogates.py
#
# Created: Oct 2024, M. Clarke
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# IMPORT
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# package imports
from scipy.interpolate import RegularGridInterpolator
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# build_AVL_surrogates
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[docs]
def build_AVL_surrogates(aerodynamics):
"""Build a surrogate using sample evaluation results.
Assumptions:
None
Source:
None
Args:
aerodynamics : VLM analysis [unitless]
Returns:
None
"""
surrogates = aerodynamics.surrogates
training = aerodynamics.training
AoA_data = training.angle_of_attack
mach_data = training.Mach
CL_data = training.coefficients[0,:,:]
CDi_data = training.coefficients[1,:,:]
e_data = training.coefficients[2,:,:]
CM_data = training.coefficients[3,:,:]
Cm_alpha_data = training.coefficients[4,:,:]
Cn_beta_data = training.coefficients[5,:,:]
NP_data = training.coefficients[6,:,:]
surrogates.lift_coefficient = RegularGridInterpolator((AoA_data, mach_data), CL_data ,method = 'linear', bounds_error=False, fill_value=None)
surrogates.drag_coefficient = RegularGridInterpolator((AoA_data, mach_data), CDi_data ,method = 'linear', bounds_error=False, fill_value=None)
surrogates.span_efficiency_factor = RegularGridInterpolator((AoA_data, mach_data), e_data ,method = 'linear', bounds_error=False, fill_value=None)
surrogates.moment_coefficient = RegularGridInterpolator((AoA_data, mach_data), CM_data ,method = 'linear', bounds_error=False, fill_value=None)
surrogates.Cm_alpha_moment_coefficient = RegularGridInterpolator((AoA_data, mach_data), Cm_alpha_data,method = 'linear', bounds_error=False, fill_value=None)
surrogates.Cn_beta_moment_coefficient = RegularGridInterpolator((AoA_data, mach_data), Cn_beta_data ,method = 'linear', bounds_error=False, fill_value=None)
surrogates.neutral_point = RegularGridInterpolator((AoA_data, mach_data), NP_data ,method = 'linear', bounds_error=False, fill_value=None)
return
