python3 compatibility

gpkitmodels/GP/aircraft/engine/DF70/fitDF70.py

@@ -1,3 +1,4 @@
+from __future__ import print_function
 import pandas as pd
 import numpy as np
 from numpy import logspace, log, log10
@@ -24,7 +25,7 @@
 K = 2
 
 cstrt, rmserror = fit(x, y, K, Type)
-print "RMS error = %.4f" % rmserror
+print("RMS error = %.4f" % rmserror)
 yfit = cstrt.evaluate(x)
 
 fig, ax = plt.subplots()
@@ -50,7 +51,7 @@
 K = 2
 
 cstrt, rmserror = fit(x,y,K,Type)
-print "RMS error = %.4f" % rmserror
+print("RMS error = %.4f" % rmserror)
 yfit = cstrt.evaluate(x)
 
 fig, ax = plt.subplots()
@@ -73,7 +74,7 @@
 Type = 'SMA'
 K = 1
 cstrt, rmserror = fit(x,y,K,Type)
-print "RMS error = %.4f" % rmserror
+print("RMS error = %.4f" % rmserror)
 yfit = cstrt.evaluate(x)
 
 fig, ax = plt.subplots()
@@ -106,7 +107,7 @@
 
 A = np.vstack([x, np.ones(len(x))]).T
 m, c = np.linalg.lstsq(A, y)[0]
-print "Equation: y = %.4gx + %.4f" % (m, c)
+print("Equation: y = %.4gx + %.4f" % (m, c))
 fig, ax = plt.subplots()
 ax.plot(x, y, 'o', label='RCV Engine Data', markerfacecolor="None")
 ax.plot(x, m*x + c, label='Fitted Line')

gpkitmodels/GP/aircraft/engine/df70.py

@@ -1,4 +1,5 @@
 " engine_model.py "
+from builtins import zip
 from gpkit import Model, Variable, units
 
 class DF70(Model):

gpkitmodels/GP/aircraft/engine/gas_engine.py

@@ -1,4 +1,5 @@
 " engine_model.py "
+from builtins import zip
 from gpkit import Model, Variable, units
 import os
 import pandas as pd

gpkitmodels/GP/aircraft/fuselage/cylindrical_fuselage.py

@@ -1,8 +1,8 @@
 " cylindrical fuselage.py "
 import numpy as np
 from gpkit import Variable, Model
-from fuel_tank import FuelTank
-from fuselage_skin import FuselageSkin
+from .fuel_tank import FuelTank
+from .fuselage_skin import FuselageSkin
 
 class Fuselage(Model):
     "The thing that carries the fuel, engine, and payload"
@@ -88,4 +88,3 @@ def setup(self, static, state):
             ]
 
         return constraints
-

gpkitmodels/GP/aircraft/fuselage/fuselage_profile_drag/fusedragfit.py

@@ -1,4 +1,5 @@
 " fuselage drag fits "
+from builtins import zip
 import pandas as pd
 import numpy as np
 import matplotlib.pyplot as plt

gpkitmodels/GP/aircraft/motor/motor_test.py

@@ -1,8 +1,8 @@
 from gpkit import Model, parse_variables, SignomialsEnabled, SignomialEquality, units
-from motor import Propulsor, Motor, MotorPerf
+from gpkitmodels.GP.aircraft.motor.motor import Propulsor, Motor, MotorPerf
 from gpkitmodels.GP.aircraft.prop.propeller import Propeller, ActuatorProp
-from gpkitmodels.SP.aircraft.prop.propeller import BladeElementProp
 from gpkitmodels.GP.aircraft.wing.wing_test import FlightState
+from gpkitmodels.SP.aircraft.prop.propeller import BladeElementProp
 
 class Propulsor_Test(Model):
     """Propulsor Test Model
@@ -47,7 +47,7 @@ def setup(self):
 def actuator_propulsor_test():
     test = Actuator_Propulsor_Test()
     test.solve()
-    
+
 def ME_propulsor_test():
     test = BladeElement_Propulsor_Test()
     sol = test.localsolve()
@@ -102,6 +102,6 @@ def test():
     actuator_propulsor_test()
     propulsor_test()
     ME_propulsor_test()
-    
+
 if __name__ == "__main__":
     test()

gpkitmodels/GP/aircraft/prop/arccos_fit.py

@@ -1,3 +1,4 @@
+from __future__ import print_function
 import unittest
 from numpy import log, exp, log10, vstack
 from numpy import arccos,arange
@@ -10,4 +11,4 @@
 K = 1
 
 cstrt, rmsErr = fit(x,y,K,"SMA")
-print rmsErr
+print(rmsErr)

gpkitmodels/GP/aircraft/tail/tailpolars/naca_cl0fits.py

@@ -1,4 +1,6 @@
 "naca_polarfits.py"
+from builtins import zip
+from builtins import range
 import numpy as np
 import pandas as pd
 import matplotlib.pyplot as plt
@@ -85,7 +87,7 @@ def plot_fits(naca_range, re_range):
     return fig, ax
 
 if __name__ == "__main__":
-    Re = range(200, 950, 50)
+    Re = list(range(200, 950, 50))
     NACA = ["0005", "0008", "0009", "0010", "0015", "0020"]
     X, Y = fit_setup(NACA, Re) # call fit(X, Y, 4, "SMA") to get fit
     F, A = plot_fits(NACA, Re)

gpkitmodels/GP/aircraft/wing/arctan_fit.py

@@ -1,3 +1,4 @@
+from __future__ import print_function
 from gpfit.fit import fit
 import os
 import matplotlib.pyplot as plt
@@ -15,7 +16,7 @@ def arctanfit():
 
     cn, err = fit(x, y, 1, "MA")
     rm = err
-    print "RMS error: %.4f" % rm
+    print("RMS error: %.4f" % rm)
 
     yfit = cn.evaluate(x)
     df = cn.get_dataframe()

gpkitmodels/GP/aircraft/wing/jho1polars/jho1_polarfits.py

@@ -1,4 +1,6 @@
 "jho1_polarfits.py"
+from builtins import zip
+from builtins import range
 import numpy as np
 import pandas as pd
 import matplotlib.pyplot as plt
@@ -77,7 +79,7 @@ def plot_fits(re):
     return fig, ax, fig1
 
 if __name__ == "__main__":
-    Re = range(200, 750, 50)
+    Re = list(range(200, 750, 50))
     X, Y = fit_setup(Re) # call fit(X, Y, 4, "SMA") to get fit
     F, A, F1 = plot_fits([300, 350, 400, 450, 500])
     F.savefig("jho1polarfit1.pdf", bbox_inches="tight")

gpkitmodels/GP/aircraft/wing/wing.py

@@ -1,4 +1,5 @@
 " wing.py "
+from builtins import range
 from os import sep
 from os.path import abspath, dirname
 import numpy as np

gpkitmodels/GP/materials/__init__.py

@@ -1,5 +1,5 @@
-from composite import CFRPFabric, CFRPUD, Kevlar
-from foam import FoamHD, FoamLD
+from .composite import CFRPFabric, CFRPUD, Kevlar
+from .foam import FoamHD, FoamLD
 
 cfrpfabric = CFRPFabric()
 cfrpud = CFRPUD()

gpkitmodels/SP/SimPleAC/SimPleAC.py

@@ -1,3 +1,4 @@
+from __future__ import print_function
 from gpkit import Model, Variable, SignomialsEnabled, VarKey, units
 import numpy as np
 import matplotlib.pyplot as plt
@@ -97,4 +98,4 @@ def test():
     m = SimPleAC()
     m.cost = m['W_f'] 
     sol = m.localsolve(verbosity = 4)
-    print sol.table()
+    print(sol.table())

gpkitmodels/SP/SimPleAC/SimPleAC_multimission.py

@@ -1,7 +1,8 @@
+from builtins import range
 import numpy as np
 from gpkit import Model, Variable, SignomialsEnabled, SignomialEquality, \
     VarKey, units, Vectorize, settings
-from SimPleAC_mission import Mission, SimPleAC
+from gpkitmodels.SP.SimPleAC.SimPleAC_mission import Mission, SimPleAC
 from gpkitmodels.SP.atmosphere.atmosphere import Atmosphere
 
 # SimPleAC with multimission design (updated 5/31/2019, by Berk Ozturk)
@@ -80,4 +81,3 @@ def test():
 
     m.cost = (m.missions[0]['W_{f_m}']*units('1/N') + m.missions[1]['C_m']*m.missions[1]['t_m'])
     sol = m.localsolve(verbosity = 2)
-

gpkitmodels/SP/aircraft/prop/dae51polars/dae51_polarfits.py

@@ -1,4 +1,7 @@
 "dae51_polarfits.py"
+from __future__ import print_function
+from builtins import zip
+from builtins import range
 import numpy as np
 import pandas as pd
 import matplotlib.pyplot as plt
@@ -108,7 +111,7 @@ def plot_fits(re, cnstr, x, y):
     X, Y = fit_setup(Re) # call fit(X, Y, 4, "SMA") to get fit
     np.random.seed(0)
     cn, err = fit(X, Y, 3, "SMA")
-    print "RMS error: %.5f" % err
+    print("RMS error: %.5f" % err)
     df = cn.get_dataframe()
     if GENERATE:
         path = os.path.dirname(inspect.getfile(ActuatorProp))

gpkitmodels/SP/aircraft/prop/propeller.py

@@ -1,4 +1,5 @@
 " propeller model "
+from builtins import range
 from numpy import pi
 from gpkit import Model, Variable,Vectorize,parse_variables, SignomialsEnabled, SignomialEquality
 from gpkit.constraints.tight import Tight as TCS

gpkitmodels/SP/atmosphere/atmosphere.py

@@ -1,3 +1,4 @@
+from __future__ import print_function
 from gpkit import Model, Variable, SignomialsEnabled, SignomialEquality, VarKey, units
 from gpkit.constraints.bounded import Bounded
 from gpkit import Vectorize
@@ -60,4 +61,4 @@ def setup(self):
     m.substitutions.update({'h':5000*units('m')})
     m.cost = m['\\mu']*m['\\rho']
     sol = m.localsolve(verbosity = 3)
-    print sol.table()
+    print(sol.table())

gpkitmodels/misc/Moment of Inertia (cylindrical beam)/moi.py

@@ -1,3 +1,3 @@
 "get the python code from the markdown file"
 from gpkit.tools import mdparse
-exec mdparse("moi.md")
+exec(mdparse("moi.md"))

gpkitmodels/misc/Net Present Value/npv.py

@@ -1,3 +1,3 @@
 "get the python code from the markdown file"
 from gpkit.tools import mdparse
-exec mdparse("npv.md")
+exec(mdparse("npv.md"))

gpkitmodels/misc/Raymer Weights/Blended Wing-Body/Raymer_Weights_Model.py

@@ -1,5 +1,6 @@
 # Below is a Weights breakdown for the Blended wing body.  This method is GP Compatible!
 
+from builtins import range
 from gpkit import VectorVariable, Variable, Model, units
 import numpy as np
 from gpkit.tools import te_exp_minus1
@@ -39,7 +40,7 @@ def secant(x, nterm):
                        69348874393137901,
                        15514534163557086905] )
     if nterm > 12:
-        n_extend = np.asarray(range(13, nterm+1))
+        n_extend = np.asarray(list(range(13, nterm+1)))
         E2n_add = (8 * np.sqrt(n_extend/np.pi) 
                       * (4*n_extend/(np.pi * np.exp(1)))**(2*n_extend))
         E2n = np.append(E2n, E2n_add)

gpkitmodels/tools/fit_constraintset.py

@@ -1,8 +1,12 @@
+from __future__ import print_function
+from builtins import str
+from builtins import zip
+from builtins import range
+import numpy as np
 from gpkit import ConstraintSet
 from gpkit import Variable, NomialArray
 from gpkit.small_scripts import unitstr
-from xfoilWrapper import blind_call, single_cl
-import numpy as np
+from .xfoilWrapper import blind_call, single_cl
 
 class FitCS(ConstraintSet):
     def __init__(self, df, ivar, dvars, nobounds=False, err_margin=False, airfoil=False):
@@ -107,7 +111,7 @@ def process_result(self, result, TOL=0.03):
                 elif "naca" in self.airfoil:
                     topline = self.airfoil + "\n"
                 else:
-                    print "Bad airfoil specified"
+                    print("Bad airfoil specified")
             else:
                 runxfoil = False
             bndwrn = True
@@ -128,12 +132,12 @@ def process_result(self, result, TOL=0.03):
                 try:
                     x = blind_call(topline, cl, re, 0.0)
                     if "VISCAL:  Convergence failed" in x:
-                        print "Convergence Warning: %s" % failmsg
+                        print("Convergence Warning: %s" % failmsg)
                         cd, cl = cdgp, 1.0
                     else:
                         cd, cl = x[0], x[1]
                 except:
-                    print "Unable to start Xfoil: %s" % failmsg
+                    print("Unable to start Xfoil: %s" % failmsg)
                     cd, cl = cdgp, 1.0
 
                 err = 1 - cdgp/cd
@@ -142,7 +146,7 @@ def process_result(self, result, TOL=0.03):
                            " Xfoil cd=%.6f, GP sol cd=%.6f" %
                            (", ".join(d.descr["models"]), err, re, cl, cd,
                             cdgp))
-                    print "Warning: %s" % msg
+                    print("Warning: %s" % msg)
                 else:
                     bndwrn = False
 
@@ -165,4 +169,4 @@ def process_result(self, result, TOL=0.03):
                                + " %s bound. Solution is %.4f but"
                                " bound is %.4f" %
                                (direct, num, bnd))
-                        print "Warning: " + msg
+                        print("Warning: " + msg)

gpkitmodels/tools/ipynb2module.py

@@ -1,7 +1,9 @@
 
 "tool for importing ipython notebooks as modules"
+from __future__ import print_function
 
 
+from builtins import object
 import io, os, sys, types
 
 # Import Modules

gpkitmodels/tools/summing_constraintset.py

@@ -1,4 +1,5 @@
 " helpers.py "
+from builtins import zip
 import numpy as np
 from gpkit import ConstraintSet, Variable
 

gpkitmodels/tools/xfoilWrapper.py

@@ -1,3 +1,5 @@
+from __future__ import print_function
+from builtins import range
 import subprocess
 import numpy as np
 import scipy.optimize as spo
@@ -68,7 +70,7 @@ def single_cl(CL, Re = 1e7, M = 0.0, airfoil=[], pathname = "/home/ckarcher/Xfoi
         elif ('naca' == airfoil.lower()[0:4]) and (len(airfoil)==8):
             topline = airfoil + ' \n'
     else:
-        print "Error: Invalid airfoil passed into XFOIL.  Defaulting to a NACA0012."
+        print("Error: Invalid airfoil passed into XFOIL.  Defaulting to a NACA0012.")
         topline = 'naca0012 \n'
 
     initial_list = np.linspace(sample_min,sample_max,num_samples).tolist()

setup.py

@@ -43,7 +43,7 @@
     author="MIT Department of Aeronautics and Astronautics",
     author_email="gpkit@mit.edu",
     url="https://www.github.com/hoburg/gpkit-models",
-    install_requires=["numpy>=1.12", "scipy", "pint"],
+    install_requires=["numpy>=1.12", "scipy", "pint", "future"],
     version="0.0.0.0",
     packages=find_packages(),
     package_data={"gpkitmodels": ["GP/aircraft/wing/*.csv",