# Path: gpkitmodels/GP/aircraft/wing/wing.py
# class Wing(Model):
#     """
#     Wing Model
# 
#     Variables
#     ---------
#     W                   [lbf]       wing weight
#     mfac        1.2     [-]         wing weight margin factor
# 
#     SKIP VERIFICATION
# 
#     Upper Unbounded
#     ---------------
#     W, planform.tau (if not sparJ)
# 
#     Lower Unbounded
#     ---------------
#     planform.b, spar.Sy (if sparModel), spar.J (if sparJ)
# 
#     LaTex Strings
#     -------------
#     mfac                m_{\\mathrm{fac}}
# 
#     """
# 
#     sparModel = CapSpar
#     fillModel = WingCore
#     flight_model = WingAero
#     skinModel = WingSkin
#     sparJ = False
# 
#     @parse_variables(__doc__, globals())
#     def setup(self, N=5):
#         self.N = N
#         self.planform = Planform(N)
#         self.components = []
# 
#         if self.skinModel:
#             self.skin = self.skinModel(self.planform)
#             self.components.extend([self.skin])
#         if self.sparModel:
#             self.spar = self.sparModel(N, self.planform)
#             self.components.extend([self.spar])
#             self.sparJ = hasattr(self.spar, "J")
#         if self.fillModel:
#             self.foam = self.fillModel(self.planform)
#             self.components.extend([self.foam])
# 
#         constraints = [W/mfac >= sum(c["W"] for c in self.components)]
# 
#         return constraints, self.planform, self.components
# 
# Path: gpkitmodels/GP/aircraft/prop/propeller.py
# class ActuatorProp(Model):
#     """ Propeller Model
# 
#     Variables
#     ---------
#     T                       [lbf]       thrust
#     Tc                      [-]         coefficient of thrust
#     etaadd     .7           [-]         swirl and nonuniformity losses
#     etav       .85          [-]         viscous losses
#     etai                    [-]         inviscid losses
#     eta                     [-]         overall efficiency
#     z1         self.helper  [-]         efficiency helper 1
#     z2                      [-]         efficiency helper 2
#     lam                     [-]         advance ratio
#     CT                      [-]         thrust coefficient
#     CP                      [-]         power coefficient
#     Q                       [N*m]       torque
#     omega                   [rpm]       propeller rotation rate
#     omega_max  10000        [rpm]       max rotation rate
#     P_shaft                 [kW]        shaft power
#     M_tip      .5           [-]         Tip mach number
#     a          295          [m/s]       Speed of sound at altitude
#     """
# 
#     def helper(self, c):
#         return 2. - 1./c(self.etaadd)
# 
#     @parse_variables(__doc__, globals())
#     def setup(self, static, state):
#         V = state.V
#         rho = state.rho
#         R = static.R
# 
#         constraints = [eta <= etav*etai,
#                        Tc >= T/(0.5*rho*V**2*pi*R**2),
#                        z2 >= Tc + 1,
#                        etai*(z1 + z2**0.5/etaadd) <= 2,
#                        lam >= V/(omega*R),
#                        CT >= Tc*lam**2,
#                        CP <= Q*omega/(.5*rho*(omega*R)**3*pi*R**2),
#                        eta >= CT*lam/CP,
#                        omega <= omega_max,
#                        P_shaft == Q*omega,
#                        (M_tip*a)**2 >= (omega*R)**2 + V**2,
#                        static.T_m >= T
#                       ]
#         return constraints


from builtins import zip
from builtins import range
from gpfit.fit import fit
from gpkitmodels.GP.aircraft.wing.wing import Wing
from gpkitmodels.GP.aircraft.prop.propeller import ActuatorProp
import numpy as np
import pandas as pd
import matplotlib.pyplot as plt
import sys
import inspect
import os
        data[t] = []

    for l in lines[start+1:]:
        for i, v in enumerate(l.split(" ")[1:]):
            data[titles[i]].append(v)

    df = pd.DataFrame(data)
    return df

def fit_setup(Re_range):
    "set up x and y parameters for gp fitting"
    CL = []
    CD = []
    RE = []
    fig, ax = plt.subplots()
    for r in Re_range:
        dataf = text_to_df("dae51.ncrit09.Re%dk.pol" % r)
        if r < 150:
            cl = dataf["CL"].values.astype(np.float)
            cd = dataf["CD"].values.astype(np.float)
            CL.append(np.hstack([cl[cl >= 1.0]]*1))
            CD.append(np.hstack([cd[cl >= 1.0]]*1))
        elif r < 200:
            cl = dataf["CL"].values.astype(np.float)
            cd = dataf["CD"].values.astype(np.float)
            CL.append(cl[cl >= 0.9])
            CD.append(cd[cl >= 0.9])
        else:
            CL.append(dataf["CL"].values.astype(np.float))
            CD.append(dataf["CD"].values.astype(np.float))

# Path: gpkitmodels/GP/aircraft/wing/wing.py
# class Wing(Model):
#     """
#     Wing Model
# 
#     Variables
#     ---------
#     W                   [lbf]       wing weight
#     mfac        1.2     [-]         wing weight margin factor
# 
#     SKIP VERIFICATION
# 
#     Upper Unbounded
#     ---------------
#     W, planform.tau (if not sparJ)
# 
#     Lower Unbounded
#     ---------------
#     planform.b, spar.Sy (if sparModel), spar.J (if sparJ)
# 
#     LaTex Strings
#     -------------
#     mfac                m_{\\mathrm{fac}}
# 
#     """
# 
#     sparModel = CapSpar
#     fillModel = WingCore
#     flight_model = WingAero
#     skinModel = WingSkin
#     sparJ = False
# 
#     @parse_variables(__doc__, globals())
#     def setup(self, N=5):
#         self.N = N
#         self.planform = Planform(N)
#         self.components = []
# 
#         if self.skinModel:
#             self.skin = self.skinModel(self.planform)
#             self.components.extend([self.skin])
#         if self.sparModel:
#             self.spar = self.sparModel(N, self.planform)
#             self.components.extend([self.spar])
#             self.sparJ = hasattr(self.spar, "J")
#         if self.fillModel:
#             self.foam = self.fillModel(self.planform)
#             self.components.extend([self.foam])
# 
#         constraints = [W/mfac >= sum(c["W"] for c in self.components)]
# 
#         return constraints, self.planform, self.components
# 
# Path: gpkitmodels/GP/aircraft/prop/propeller.py
# class ActuatorProp(Model):
#     """ Propeller Model
# 
#     Variables
#     ---------
#     T                       [lbf]       thrust
#     Tc                      [-]         coefficient of thrust
#     etaadd     .7           [-]         swirl and nonuniformity losses
#     etav       .85          [-]         viscous losses
#     etai                    [-]         inviscid losses
#     eta                     [-]         overall efficiency
#     z1         self.helper  [-]         efficiency helper 1
#     z2                      [-]         efficiency helper 2
#     lam                     [-]         advance ratio
#     CT                      [-]         thrust coefficient
#     CP                      [-]         power coefficient
#     Q                       [N*m]       torque
#     omega                   [rpm]       propeller rotation rate
#     omega_max  10000        [rpm]       max rotation rate
#     P_shaft                 [kW]        shaft power
#     M_tip      .5           [-]         Tip mach number
#     a          295          [m/s]       Speed of sound at altitude
#     """
# 
#     def helper(self, c):
#         return 2. - 1./c(self.etaadd)
# 
#     @parse_variables(__doc__, globals())
#     def setup(self, static, state):
#         V = state.V
#         rho = state.rho
#         R = static.R
# 
#         constraints = [eta <= etav*etai,
#                        Tc >= T/(0.5*rho*V**2*pi*R**2),
#                        z2 >= Tc + 1,
#                        etai*(z1 + z2**0.5/etaadd) <= 2,
#                        lam >= V/(omega*R),
#                        CT >= Tc*lam**2,
#                        CP <= Q*omega/(.5*rho*(omega*R)**3*pi*R**2),
#                        eta >= CT*lam/CP,
#                        omega <= omega_max,
#                        P_shaft == Q*omega,
#                        (M_tip*a)**2 >= (omega*R)**2 + V**2,
#                        static.T_m >= T
#                       ]
#         return constraints


# Path: gpkitmodels/SP/aircraft/prop/dae51polars/dae51_polarfits.py
from builtins import zip
from builtins import range
from gpfit.fit import fit
from gpkitmodels.GP.aircraft.wing.wing import Wing
from gpkitmodels.GP.aircraft.prop.propeller import ActuatorProp
import numpy as np
import pandas as pd
import matplotlib.pyplot as plt
import sys
import inspect
import os

        data[t] = []

    for l in lines[start+1:]:
        for i, v in enumerate(l.split(" ")[1:]):
            data[titles[i]].append(v)

    df = pd.DataFrame(data)
    return df

def fit_setup(Re_range):
    "set up x and y parameters for gp fitting"
    CL = []
    CD = []
    RE = []
    fig, ax = plt.subplots()
    for r in Re_range:
        dataf = text_to_df("dae51.ncrit09.Re%dk.pol" % r)
        if r < 150:
            cl = dataf["CL"].values.astype(np.float)
            cd = dataf["CD"].values.astype(np.float)
            CL.append(np.hstack([cl[cl >= 1.0]]*1))
            CD.append(np.hstack([cd[cl >= 1.0]]*1))
        elif r < 200:
            cl = dataf["CL"].values.astype(np.float)
            cd = dataf["CD"].values.astype(np.float)
            CL.append(cl[cl >= 0.9])
            CD.append(cd[cl >= 0.9])
        else:
            CL.append(dataf["CL"].values.astype(np.float))
            CD.append(dataf["CD"].values.astype(np.float))

        ax.plot(dataf["CL"].values.astype(np.float), dataf["CD"].values.astype(np.float))