def summarize(interface): # Unpack inputs = interface.inputs vehicle = interface.configs.base results = interface.results mission_profile = results.sizing_loop # Weights operating_empty = vehicle.mass_properties.operating_empty payload = vehicle.mass_properties.payload # pack summary = SUAVE.Core.Results() # TOFL for MTOW @ SL, ISA summary.total_range =mission_profile.segments[-1].conditions.frames.inertial.position_vector[-1,0] summary.GLW =mission_profile.segments[-1].conditions.weights.total_mass[-1,0] summary.takeoff_field_length =results.field_length.takeoff summary.landing_field_length =results.field_length.landing summary.climb_alt_constr =inputs.climb_alt_fraction_1-inputs.climb_alt_fraction_2 # MZFW margin calculation #summary.max_zero_fuel_margin = max_zero_fuel - (operating_empty + payload) # fuel margin calculation # Print outs printme = Data() printme.weight_empty = operating_empty printme.total_range =summary.total_range/Units.nautical_miles printme.GLW =summary.GLW printme.tofl = summary.takeoff_field_length printme.lfl = summary.landing_field_length #printme.range_max = summary.range_max_nmi #printme.max_zero_fuel_margin = summary.max_zero_fuel_margin #printme.available_fuel_margin = summary.available_fuel_margin print "RESULTS" print printme inputs = interface.inputs import datetime fid = open('Results.dat','a') fid.write('{:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; '.format( \ inputs.aspect_ratio, inputs.reference_area, #inputs.sweep, inputs.wing_thickness, #operating_empty , summary.takeoff_field_length , summary.landing_field_length )) fid.write(datetime.datetime.now().strftime("%I:%M:%S")) fid.write('\n') ## print interface.configs.takeoff.maximum_lift_coefficient return summary