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("-------------------------------------------")