Both stages of futurize.

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

@@ -1,4 +1,5 @@
 " cylindrical fuselage.py "
+from __future__ import absolute_import
 import numpy as np
 from gpkit import Variable, Model
 from fuel_tank import FuelTank

gpkitmodels/GP/aircraft/fuselage/elliptical_fuselage.py

@@ -16,7 +16,7 @@ class FuselageAero(Model):
 
     """
     def setup(self, static, state):
-        exec parse_variables(FuselageAero.__doc__)
+        exec(parse_variables(FuselageAero.__doc__))
 
         V = state.V
         rho = state.rho
@@ -55,7 +55,7 @@ class Fuselage(Model):
     flight_model = FuselageAero
 
     def setup(self):
-        exec parse_variables(Fuselage.__doc__)
+        exec(parse_variables(Fuselage.__doc__))
 
         rhocfrp = self.material.rho
         tmin = self.material.tmin

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.py

@@ -22,7 +22,7 @@ class MotorPerf(Model):
     v                       [V]             woltage
     """
     def setup(self, static, state):
-        exec parse_variables(MotorPerf.__doc__)
+        exec(parse_variables(MotorPerf.__doc__))
 
         Kv = static.Kv
         R  = static.R
@@ -56,7 +56,7 @@ class Motor(Model):
     flight_model = MotorPerf
 
     def setup(self):
-        exec parse_variables(Motor.__doc__)
+        exec(parse_variables(Motor.__doc__))
 
         constraints = [W >= Qstar*Qmax*g,
                        Kv >= Kv_min,
@@ -70,7 +70,7 @@ class PropulsorPerf(Model):
     """
 
     def setup(self, static, state):
-        exec parse_variables(PropulsorPerf.__doc__)
+        exec(parse_variables(PropulsorPerf.__doc__))
         self.prop = static.prop.flight_model(static.prop, state)
         self.motor = static.motor.flight_model(static.motor, state)
 
@@ -95,7 +95,7 @@ class Propulsor(Model):
 
 
     def setup(self):
-        exec parse_variables(Propulsor.__doc__)
+        exec(parse_variables(Propulsor.__doc__))
 
         Propeller.flight_model = self.prop_flight_model
         self.prop = Propeller()

gpkitmodels/GP/aircraft/motor/motor_test.py

@@ -1,3 +1,4 @@
+from __future__ import absolute_import
 from gpkit import Model, parse_variables, SignomialsEnabled, SignomialEquality, units
 from motor import Propulsor, Motor, MotorPerf
 from gpkitmodels.GP.aircraft.prop.propeller import Propeller, ActuatorProp

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/prop/propeller.py

@@ -34,7 +34,7 @@ def helper(self, c):
         return 2. - 1./c(self.etaadd)
 
     def setup(self, static, state):
-        exec parse_variables(ActuatorProp.__doc__)
+        exec(parse_variables(ActuatorProp.__doc__))
 
         V = state.V
         rho = state.rho
@@ -74,6 +74,6 @@ class Propeller(Model):
     flight_model = ActuatorProp
 
     def setup(self, N = 5):
-        exec parse_variables(Propeller.__doc__)
+        exec(parse_variables(Propeller.__doc__))
         self.N = N
         return [W >= K*T_m*R**2]

gpkitmodels/GP/aircraft/tail/empennage.py

@@ -38,7 +38,7 @@ class Empennage(Model):
 
     """
     def setup(self, N=2):
-        exec parse_variables(Empennage.__doc__)
+        exec(parse_variables(Empennage.__doc__))
 
         self.htail = HorizontalTail()
         self.hSparModel = self.htail.sparModel

gpkitmodels/GP/aircraft/tail/horizontal_tail.py

@@ -41,7 +41,7 @@ class HorizontalTail(Wing):
     sparModel = None
 
     def setup(self, N=3):
-        exec parse_variables(HorizontalTail.__doc__)
+        exec(parse_variables(HorizontalTail.__doc__))
 
         self.ascs = Wing.setup(self, N)
         self.planform.substitutions.update(

gpkitmodels/GP/aircraft/tail/tail_aero.py

@@ -30,7 +30,7 @@ class TailAero(Model):
     """
     def setup(self, static, state):
         self.state = state
-        exec parse_variables(TailAero.__doc__)
+        exec(parse_variables(TailAero.__doc__))
 
         cmac = self.cmac = static.planform.cmac
         b = self.b = static.planform.b

gpkitmodels/GP/aircraft/tail/tail_boom.py

@@ -31,7 +31,7 @@ class TailBoomAero(Model):
     """
     def setup(self, static, state):
         self.state = state
-        exec parse_variables(TailBoomAero.__doc__)
+        exec(parse_variables(TailBoomAero.__doc__))
 
         l = self.l = static.l
         rho = self.rho = state.rho
@@ -57,7 +57,7 @@ class TailBoomState(Model):
 
     """
     def setup(self):
-        exec parse_variables(TailBoomState.__doc__)
+        exec(parse_variables(TailBoomState.__doc__))
 
 
 class VerticalBoomTorsion(Model):
@@ -82,7 +82,7 @@ class VerticalBoomTorsion(Model):
 
     """
     def setup(self, tailboom, vtail, state):
-        exec parse_variables(VerticalBoomTorsion.__doc__)
+        exec(parse_variables(VerticalBoomTorsion.__doc__))
 
         J = self.J = tailboom.J
         d0 = self.d0 = tailboom.d
@@ -133,7 +133,7 @@ def setup(self, tailboom, htail, state):
         self.state = state
         self.htail = htail
         self.tailboom = tailboom
-        exec parse_variables(TailBoomBending.__doc__)
+        exec(parse_variables(TailBoomBending.__doc__))
 
         Beam.qbarFun = [1e-10]*N
         Beam.SbarFun = [1.]*N
@@ -188,7 +188,7 @@ class TailBoom(TubeSpar):
 
     def setup(self, N=5):
         self.N = N
-        exec parse_variables(TailBoom.__doc__)
+        exec(parse_variables(TailBoom.__doc__))
         self.spar = super(TailBoom, self).setup(N, self)
 
         if self.secondaryWeight:

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/tail/tube_spar.py

@@ -41,7 +41,7 @@ class TubeSpar(Model):
     material = cfrpfabric
 
     def setup(self, N, surface):
-        exec parse_variables(TubeSpar.__doc__)
+        exec(parse_variables(TubeSpar.__doc__))
 
         deta = surface.deta
         tmin = self.material.tmin

gpkitmodels/GP/aircraft/tail/vertical_tail.py

@@ -36,7 +36,7 @@ class VerticalTail(Wing):
     sparModel = None
 
     def setup(self, N=3):
-        exec parse_variables(VerticalTail.__doc__)
+        exec(parse_variables(VerticalTail.__doc__))
 
         self.ascs = Wing.setup(self, N)
         self.planform.substitutions.update(

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/boxspar.py

@@ -61,7 +61,7 @@ class BoxSpar(Model):
 
     def setup(self, N, surface):
         self.surface = surface
-        exec parse_variables(BoxSpar.__doc__)
+        exec(parse_variables(BoxSpar.__doc__))
 
         b = self.b = surface.b
         cave = self.cave = surface.cave

gpkitmodels/GP/aircraft/wing/capspar.py

@@ -56,7 +56,7 @@ class CapSpar(Model):
 
     def setup(self, N, surface):
         self.surface = surface
-        exec parse_variables(CapSpar.__doc__)
+        exec(parse_variables(CapSpar.__doc__))
 
         cave = self.cave = surface.cave
         b = self.b = surface.b

gpkitmodels/GP/aircraft/wing/gustloading.py

@@ -43,7 +43,7 @@ def return_cosm1(self, c):
         return hstack([adnumber(1e-10), 1-array(cos(eta[1:]*pi/2))])
 
     def setup(self, wing, state, out=False):
-        exec parse_variables(GustL.__doc__)
+        exec(parse_variables(GustL.__doc__))
         self.load = SparLoading.setup(self, wing, state, out=out)
 
         cbar = self.wing.planform.cbar

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/sparloading.py

@@ -52,7 +52,7 @@ def new_qbarFun(self, c):
 
     def setup(self, wing, state, out=False):
         self.wing = wing
-        exec parse_variables(SparLoading.__doc__)
+        exec(parse_variables(SparLoading.__doc__))
 
         b = self.b = self.wing.planform.b
         I = self.I = self.wing.spar.I

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
@@ -81,7 +82,7 @@ def return_cmac(self, c):
     return_deta = lambda self, c: np.diff(c(self.eta))
 
     def setup(self, N):
-        exec parse_variables(Planform.__doc__)
+        exec(parse_variables(Planform.__doc__))
 
         return [b**2 == S*AR,
                 cave == cbave*S/b,
@@ -121,7 +122,7 @@ def setup(self, static, state,
               fitdata=dirname(abspath(__file__)) + sep + "jho_fitdata.csv"):
         self.state = state
         self.static = static
-        exec parse_variables(WingAero.__doc__)
+        exec(parse_variables(WingAero.__doc__))
 
         df = pd.read_csv(fitdata)
         fd = df.to_dict(orient="records")[0]
@@ -180,7 +181,7 @@ class Wing(Model):
 
     def setup(self, N=5):
         self.N = N
-        exec parse_variables(Wing.__doc__)
+        exec(parse_variables(Wing.__doc__))
 
         self.planform = Planform(N)
         self.components = []

gpkitmodels/GP/aircraft/wing/wing_core.py

@@ -31,7 +31,7 @@ class WingCore(Model):
 
     def setup(self, surface):
         self.surface = surface
-        exec parse_variables(WingCore.__doc__)
+        exec(parse_variables(WingCore.__doc__))
 
         cave = self.cave = surface.cave
         b = self.b = surface.b

gpkitmodels/GP/aircraft/wing/wing_skin.py

@@ -36,7 +36,7 @@ class WingSkin(Model):
     material = cfrpfabric
 
     def setup(self, surface):
-        exec parse_variables(WingSkin.__doc__)
+        exec(parse_variables(WingSkin.__doc__))
 
         croot = self.croot = surface.croot
         S = self.S = surface.S
@@ -71,7 +71,7 @@ class WingSecondStruct(Model):
 
     """
     def setup(self, surface):
-        exec parse_variables(WingSecondStruct.__doc__)
+        exec(parse_variables(WingSecondStruct.__doc__))
 
         S = self.S = surface.S
 

gpkitmodels/GP/aircraft/wing/wing_test.py

@@ -19,7 +19,7 @@ class FlightState(Model):
 
     """
     def setup(self):
-        exec parse_variables(FlightState.__doc__)
+        exec(parse_variables(FlightState.__doc__))
 
         return [qne == V**2*rho*1.2]