aircraft.power_elec_chain.mto = e_power
aircraft.power_elec_chain.mcn = e_power
aircraft.power_elec_chain.mcl = e_power
aircraft.power_elec_chain.mcr = e_power
aircraft.battery.energy_cruise = 0. #unit.J_kWh(140) # J, energy stored in the battery dedicated to the cruise
aircraft.battery.energy_density = unit.J_kWh(
0.2) # J/kg, # Battery energy density
aircraft.propulsion.bli_effect = 1 #init.boundary_layer_effect()
aircraft.power_elec_chain.overall_efficiency = 0.90 # 0.90 from init.e_chain_efficiency()
# Solve the geometric coupling between airframe and engines
#------------------------------------------------------------------------------------------------------
run.aircraft_pre_design(aircraft)
# Estimate all mass and CGs
#------------------------------------------------------------------------------------------------------
run.mass_mission_adaptation(aircraft)
#run.mass_estimation(aircraft)
# Calculate all airplane performances
#------------------------------------------------------------------------------------------------------
run.performance_analysis(aircraft)
# Print relevant output
#------------------------------------------------------------------------------------------------------
altp = unit.m_ft(35000)
disa = 0
pamb, tamb, tstd, dtodz = earth.atmosphere(altp, disa)
n_pax_ref = 150
propu_config = 1
n_engine = 2
#------------------------------------------------------------------------------------------------------
perform.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach, propu_config, n_engine)
#aircraft.turboprop_engine.reference_thrust = 75000
#aircraft.wing.area = 90
print("-------------------------------------------")
print("Initialization : done")
#------------------------------------------------------------------------------------------------------
perform.aircraft_pre_design(aircraft)
print("-------------------------------------------")
print("Pre design : done")
#------------------------------------------------------------------------------------------------------
#perform.mass_estimation(aircraft)
perform.mass_mission_adaptation(aircraft)
print("-------------------------------------------")
print("Mass & CG estimation : done")
#------------------------------------------------------------------------------------------------------
perform.performance_analysis(aircraft)
print("-------------------------------------------")
