Thank you !
So, here's da thingie, as seen under Spyder Python 3.7 :
Problem is (under Part 1.2 quoted below) :
from mdo_import_helper import *
exec(import_modules('pySpline', 'tripan', 'functions'))
Error:
ModuleNotFoundError :
No module named 'mdo_import_helper'
Code :
# =======================================================================================
# Aerodynamic Analysis of a Wing
# =======================================================================================
# A generic semi-tappered wing is used for this example
# =======================================================================================
# Aerodynamic Analysis With Tripan Flow Solver
# =======================================================================================
# Part 1 : Importing Standard Python Modules
import os, sys, string, pdb, copy, time, string, re, numpy, datetime
# Set the beginning of the timer for code
t0 = datetime.datetime.now()
# _______________________________________________________________________________________
# Part 1.1 : Importing External Python Modules and setting of broadcasting variable
from mpi4py import MPI
comm = MPI.COMM_WORLD
# _______________________________________________________________________________________
# Part 1.2 : Importing Extension modules and initializing 'comm' variables
from mdo_import_helper import *
exec(import_modules('pySpline', 'tripan', 'functions'))
# _______________________________________________________________________________________
# Part 1.3 : Defining the folder for the results output
prefix = './results'
for arg in sys.argv:
# Find the prefix from the command line arguments
m = re.match('(prefix=)(.*)', arg)
if m:
prefix = m.group(2)
# Create a new directory and broadcast it to everything
if os.path.isdir(prefix):
i = 1
while os.path.isdir(os.path.join(prefix, 'Aero_Analysis_Num%d'%(i))):
i = i+1
prefix = os.path.join(prefix, 'Aero_Analysis_Num%d'%(i))
os.mkdir(prefix)
prefix = prefix + os.sep
else:
print('Prefix is not a directory!')
prefix = MPI.COMM_WORLD.bcast(prefix, root=0)
print ('Using prefix = %s'%(prefix))
# =======================================================================================
# Part 2 : Defining The Functions to set up the Tripan Object
def setUpTriPanWing(comm, trifile='geo/wing.tripan', wakefile='geo/wing.edge'):
# Set up TriPan using the files
ndownstream = 100
sym_direction = 2 # Use symmetry about the z-axis
down_dist = 150.0
time_dependent = 0 # A steady state simulation
a_wake_dir = numpy.zeros(3)
b_wake_dir = numpy.zeros(3)
a_wake_dir[1] = 1.0
b_wake_dir[2] = 1.0
# Stretch the wake downstream
wake_history = tripan.WakeHistory(ndownstream, down_dist, tripan.WakeHistory.STRETCHED)
triPan = tripan.TriPanel(comm, trifile, wakefile, wake_history, time_dependent, ndownstream, a_wake_dir, b_wake_dir, sym_direction)
npanels = triPan.getNumPanels()
triPan.setPCSizes(1.5, 150*npanels)
print('TriPan panels', npanels)
return triPan
# =======================================================================================
# Part 3 : Core of the Script for Aerodynamic Analysis With Tripan Flow Solver
# _______________________________________________________________________________________
# Part 3.1 : Setting Up the Tripan Flow Solver
# Defining The Names for the Tripan Input Files
trifile = 'geo/wing_50x100.tripan'; wakefile = 'geo/wing_50x100.wake'
edgefile = 'geo/wing_50x100.edge';
# Set Up Tripan Object
triPan = setUpTriPanWing(comm, trifile=trifile, wakefile=wakefile)
edgeinfo = tripan.TriPanEdgeInfo(edgefile)
# Set Up Tripan Solver
n_flight_cons = 1
triOpt = tripan.TriPanOpt(triPan, n_flight_cons)
# _______________________________________________________________________________________
# Part 3.2 : Defining The Design Parameters for the Atmosphere properties
Semi_Span = 15/2
# Generic atmospheric conditions for 1000m , 25 m/s with MAC as reference length
Minf = 0.0743 # Incompressible Mach number
rho = 1.11164 # Air density kg/m^3
ainf = 336.4379 # Speed of sound m/s
alpha = (4.0/180.0)*numpy.pi # Angle of attack
Vinf = Minf*ainf # Air speed
Qinf = 0.5*rho*Vinf**2 # Dynamic Pressure
# _______________________________________________________________________________________
# Part 3.3 : Solving the Aerodynamic System
# Function to get the Wing Area to compute coefficients
area_func = tripan.TriPanProjectedArea()
Area_ref = area_func.evalFunction(triPan)
print('Area_Tripan = ', Area_ref)
# Setting the Load Case, the Wing Angle of Attack and Flight Condition
load_case = 0
alpha_num = 0
fcon = tripan.FlightCondition(rho, Minf, Vinf, alpha, alpha_num, load_case)
triOpt.addFlightCondition(0, fcon)
triOpt.setFlightCondition(0)
# Setting the options for the Generalized Minimal Residual Method (GMRES) Solver
gmres_iters = 60
max_iters = 5*gmres_iters
triOpt.setGMRESIters(gmres_iters, max_iters)
triOpt.monitor()
# Solve the aerodynamic problem
triOpt.solve()
# _______________________________________________________________________________________
# Part 3.4 : Setting Up the Solution Output Files
# Setting the names for the Output Files
obj_aero_name = prefix+'wing_obj_aero.dat'
tecplot_sol_name = prefix+'wing_tripan_solution.dat'
wake_sol_name = prefix+'wing_wake_file.dat'
load_file_name = 'load_data/wing_aero_load.dat'
lift_dist_name = prefix+'wing_lift_dist.dat'
# Generating Surface solution output
triOpt.writeAeroFile(obj_aero_name)
# Generating .dat Tacplot Visualization files
out_type = 1
triPan.writeSeqTecplotFile(tecplot_sol_name, -1.0, out_type)
triPan.writeWakeFile(wake_sol_name)
# Generating Load data
triPan.writeAeroForceFile(Winf, load_file_name)
# Generating lift distribution graph
Zloc = numpy.linspace(0.01, Semi_Span)
triPan.writeLiftDistribution(lift_dist_name, Zloc)
# Evaluation of aerodynamic functions
lift_func = tripan.TriPanLift()
drag_func = tripan.TriPanDrag()
lift = triOpt.evalAeroFunc(lift_func)
drag = triOpt.evalAeroFunc(drag_func)
# Writing some outputs for user visualization
print('Lift = ', lift*Qinf*2)
print('Drag = ', drag*Qinf*2)
print('CL = ', (lift/Area_ref)*2)
print('CD = ', (drag/Area_ref)*2)
final_time = datetime.datetime.now()-t0
print('Total time spent in the aerodynamic analysis: ', final_time)
