def main():
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
# --- Vehicle definition ---
vehicle = define_vehicle()
# --- Landing Configuration ---
landing_config = vehicle.configs.takeoff
landing_config.wings['Main Wing'].flaps_angle = 30. * Units.deg
landing_config.wings['Main Wing'].slats_angle = 25. * Units.deg
# Vref_V2_ratio may be informed by user. If not, use default value (1.23)
landing_config.Vref_VS_ratio = 1.23
# CLmax for a given configuration may be informed by user
# landing_config.maximum_lift_coefficient = 2.XX
# --- Airport definition ---
airport = SUAVE.Attributes.Airports.Airport()
airport.tag = 'airport'
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
# =====================================
# Landing field length evaluation
# =====================================
w_vec = np.linspace(20000., 44000., 10)
landing_field_length = np.zeros_like(w_vec)
for id_w, weight in enumerate(w_vec):
landing_config.mass_properties.landing = weight
landing_field_length[id_w] = estimate_landing_field_length(
vehicle, landing_config, airport)
truth_LFL = np.array([
705.78061286, 766.55136124, 827.32210962, 888.092858, 948.86360638,
1009.63435476, 1070.40510314, 1131.17585152, 1191.9465999,
1252.71734828
])
LFL_error = np.max(np.abs(landing_field_length - truth_LFL))
print 'Maximum Landing Field Length Error= %.4e' % LFL_error
title = "LFL vs W"
plt.figure(1)
plt.hold
plt.plot(w_vec, landing_field_length, 'k-', label='Landing Field Length')
plt.title(title)
plt.grid(True)
legend = plt.legend(loc='lower right', shadow='true')
plt.xlabel('Weight (kg)')
plt.ylabel('Landing Field Length (m)')
assert (LFL_error < 1e-5)
return
def main():
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
# --- Vehicle definition ---
vehicle = vehicle_setup()
configs=configs_setup(vehicle)
# --- Landing Configuration ---
landing_config = configs.landing
landing_config.wings['main_wing'].flaps.angle = 30. * Units.deg
landing_config.wings['main_wing'].slats.angle = 25. * Units.deg
landing_config.wings['main_wing'].high_lift = True
# Vref_V2_ratio may be informed by user. If not, use default value (1.23)
landing_config.Vref_VS_ratio = 1.23
# CLmax for a given configuration may be informed by user
# landing_config.maximum_lift_coefficient = 2.XX
# Used defined ajust factor for maximum lift coefficient
landing_config.max_lift_coefficient_factor = 0.90
# --- Airport definition ---
airport = SUAVE.Attributes.Airports.Airport()
airport.tag = 'airport'
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
# =====================================
# Landing field length evaluation
# =====================================
w_vec = np.linspace(20000.,44000.,10)
landing_field_length = np.zeros_like(w_vec)
for id_w,weight in enumerate(w_vec):
landing_config.mass_properties.landing = weight
landing_field_length[id_w] = estimate_landing_field_length(landing_config,landing_config,airport)
truth_LFL = np.array( [ 723.67022689 , 786.82625714 , 849.98228739 , 913.13831764 , 976.29434789 , 1039.45037815 , 1102.6064084 , 1165.76243865 , 1228.9184689 , 1292.07449915])
LFL_error = np.max(np.abs(landing_field_length-truth_LFL))
print('Maximum Landing Field Length Error= %.4e' % LFL_error)
title = "LFL vs W"
plt.figure(1);
plt.plot(w_vec,landing_field_length, 'k-', label = 'Landing Field Length')
plt.title(title); plt.grid(True)
plt.figure(1); plt.plot(w_vec,truth_LFL, label = 'Landing Field Length (true)')
legend = plt.legend(loc='lower right', shadow = 'true')
plt.xlabel('Weight (kg)')
plt.ylabel('Landing Field Length (m)')
#assert( LFL_error < 1e-5 )
return
def main():
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
# --- Vehicle definition ---
vehicle = vehicle_setup()
configs=configs_setup(vehicle)
# --- Landing Configuration ---
landing_config = configs.landing
landing_config.wings['main_wing'].flaps.angle = 30. * Units.deg
landing_config.wings['main_wing'].slats.angle = 25. * Units.deg
landing_config.wings['main_wing'].high_lift = True
# Vref_V2_ratio may be informed by user. If not, use default value (1.23)
landing_config.Vref_VS_ratio = 1.23
# CLmax for a given configuration may be informed by user
# landing_config.maximum_lift_coefficient = 2.XX
# Used defined ajust factor for maximum lift coefficient
landing_config.max_lift_coefficient_factor = 0.90
# --- Airport definition ---
airport = SUAVE.Attributes.Airports.Airport()
airport.tag = 'airport'
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
# =====================================
# Landing field length evaluation
# =====================================
w_vec = np.linspace(20000.,44000.,10)
landing_field_length = np.zeros_like(w_vec)
for id_w,weight in enumerate(w_vec):
landing_config.mass_properties.landing = weight
landing_field_length[id_w] = estimate_landing_field_length(landing_config,landing_config,airport)
truth_LFL = np.array( [ 723.67022689 , 786.82625714 , 849.98228739 , 913.13831764 , 976.29434789 , 1039.45037815 , 1102.6064084 , 1165.76243865 , 1228.9184689 , 1292.07449915])
LFL_error = np.max(np.abs(landing_field_length-truth_LFL))
print 'Maximum Landing Field Length Error= %.4e' % LFL_error
title = "LFL vs W"
plt.figure(1); plt.hold
plt.plot(w_vec,landing_field_length, 'k-', label = 'Landing Field Length')
plt.title(title); plt.grid(True)
plt.figure(1); plt.plot(w_vec,truth_LFL, label = 'Landing Field Length (true)')
legend = plt.legend(loc='lower right', shadow = 'true')
plt.xlabel('Weight (kg)')
plt.ylabel('Landing Field Length (m)')
#assert( LFL_error < 1e-5 )
return
def main():
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
# --- Vehicle definition ---
vehicle = vehicle_setup()
configs=configs_setup(vehicle)
# --- Landing Configuration ---
landing_config = configs.landing
landing_config.wings['main_wing'].flaps.angle = 30. * Units.deg
landing_config.wings['main_wing'].slats.angle = 25. * Units.deg
landing_config.wings['main_wing'].high_lift = True
# Vref_V2_ratio may be informed by user. If not, use default value (1.23)
landing_config.Vref_VS_ratio = 1.23
# CLmax for a given configuration may be informed by user
# landing_config.maximum_lift_coefficient = 2.XX
# --- Airport definition ---
airport = SUAVE.Attributes.Airports.Airport()
airport.tag = 'airport'
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
# =====================================
# Landing field length evaluation
# =====================================
w_vec = np.linspace(20000.,44000.,10)
landing_field_length = np.zeros_like(w_vec)
for id_w,weight in enumerate(w_vec):
landing_config.mass_properties.landing = weight
landing_field_length[id_w] = estimate_landing_field_length(landing_config,landing_config,airport)
truth_LFL = np.array([705.78061286, 766.55136124, 827.32210962, 888.092858, 948.86360638,
1009.63435476, 1070.40510314, 1131.17585152, 1191.9465999, 1252.71734828])
LFL_error = np.max(np.abs(landing_field_length-truth_LFL))
print 'Maximum Landing Field Length Error= %.4e' % LFL_error
title = "LFL vs W"
plt.figure(1); plt.hold
plt.plot(w_vec,landing_field_length, 'k-', label = 'Landing Field Length')
plt.title(title); plt.grid(True)
legend = plt.legend(loc='lower right', shadow = 'true')
plt.xlabel('Weight (kg)')
plt.ylabel('Landing Field Length (m)')
plt.figure(2); plt.plot(w_vec,truth_LFL)
#assert( LFL_error < 1e-5 )
return
def main():
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
# --- Vehicle definition ---
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# --- Landing Configuration ---
landing_config = configs.landing
landing_config.wings[
'main_wing'].control_surfaces.flap.deflection = 30. * Units.deg
landing_config.wings[
'main_wing'].control_surfaces.slat.deflection = 25. * Units.deg
landing_config.wings['main_wing'].high_lift = True
# Vref_V2_ratio may be informed by user. If not, use default value (1.23)
landing_config.Vref_VS_ratio = 1.23
# CLmax for a given configuration may be informed by user
# Used defined ajust factor for maximum lift coefficient
analyses = base_analysis(vehicle)
analyses.aerodynamics.settings.maximum_lift_coefficient_factor = 0.90
# --- Airport definition ---
airport = SUAVE.Attributes.Airports.Airport()
airport.tag = 'airport'
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
# =====================================
# Landing field length evaluation
# =====================================
w_vec = np.linspace(20000., 44000., 10)
landing_field_length = np.zeros_like(w_vec)
for id_w, weight in enumerate(w_vec):
landing_config.mass_properties.landing = weight
landing_field_length[id_w] = estimate_landing_field_length(
landing_config, analyses, airport)
truth_LFL = np.array([
736.09211533, 800.90439737, 865.71667941, 930.52896146, 995.3412435,
1060.15352554, 1124.96580759, 1189.77808963, 1254.59037167,
1319.40265372
])
LFL_error = np.max(np.abs(landing_field_length - truth_LFL))
assert (LFL_error < 1e-6)
print('Maximum Landing Field Length Error= %.4e' % LFL_error)
title = "LFL vs W"
plt.figure(1)
plt.plot(w_vec, landing_field_length, 'k-', label='Landing Field Length')
plt.title(title)
plt.grid(True)
plt.figure(1)
plt.plot(w_vec, truth_LFL, label='Landing Field Length (true)')
legend = plt.legend(loc='lower right', shadow='true')
plt.xlabel('Weight (kg)')
plt.ylabel('Landing Field Length (m)')
#assert( LFL_error < 1e-5 )
return
def main():
# ---------------------------------------------------------------------------------------
# INITIALIZING AIRCRAFT
configs, analyses, vehicle = full_setup()
print 'full setup OK'
simple_sizing(configs)
configs.finalize()
analyses.finalize()
# ---------------------------------------------------------------------------------------
# WEIGHT ANALYSIS
weights = analyses.configs.base.weights
weights.evaluate()
print 'WEIGHTS OK'
# ---------------------------------------------------------------------------------------
# MISSION ANALYSIS
mission = analyses.missions.base
results = mission.evaluate()
print 'MISSION OK'
configs.cruise.conditions = Data()
configs.cruise.conditions = results.segments.cruise.conditions
# print weight breakdown
print_weight_breakdown(configs.base, filename='ATR72_weight_breakdown.dat')
# print parasite drag data into file - define reference condition for parasite drag
ref_condition = Data()
ref_condition.mach_number = 0.3
ref_condition.reynolds_number = 12e6
print_parasite_drag(ref_condition, configs.cruise, analyses,
'ATR72_parasite_drag.dat')
# print compressibility drag data into file
print_compress_drag(configs.cruise,
analyses,
filename='ATR72_compress_drag.dat')
# print mission breakdown
print_mission_breakdown(results, filename='ATR72_mission_breakdown.dat')
state = Data()
state.conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
)
state.numerics = SUAVE.Analyses.Mission.Segments.Conditions.Numerics()
# ---------------------------------------------------------------------------------------
# PLOT RESULTS
plot_mission(results, 0)
# ---------------------------------------------------------------------------------------
# PAYLOAD RANGE DIAGRAM
config = configs.base
cruise_segment_tag = "cruise"
reserves = [775., 1120., 1040.]
weights.mass_properties.operating_empty = weights.mass_properties.operating_empty - 239.
payloadrange = payload_range(config, mission, cruise_segment_tag, reserves)
# ---------------------------------------------------------------------------------------
# TAKE OFF FIELD LENGTH
# ---- Inputs
analyses.base = analyses.configs.base
airport = mission.airport
clb_grad = 1
altitude = [0., 6000.]
delta_isa = 0. # +23
# 1000, 1100, 1200, 1300, 1400, -, 1500, 1600
# 1200, 1300, 1400, 1500, 1600, 1700
weights_tofl = [[20062, 21044, 21954, 22801, 23000, 23452, 23754, 21200],
[18489, 19342, 20154, 20928, 21671, 22105, 21530]]
# ---- Inputs: FLAP AND SLAT DEFLECTION
flaps = [15., 0.] # Deflections inboard local
slats = [0., 0.]
# ---- Inputs: FACTOR CLMAX
configs.takeoff.max_lift_coefficient_factor = 1.189
configs.takeoff.V2_VS_ratio = 1.143
# ---- Open output file
fid = open('TOFL.txt', 'w') # Open output file
# ---- Run
for j, h in enumerate(altitude):
airport.altitude = h * Units.ft
airport.delta_isa = delta_isa
fid.write('Altitude: %4.0f ft \n' % (h))
fid.write(
'TOFL CLIMB GRADIENT THRUST L/D L/Dv2 CDasym CDwindm CL CD CG_CORRECT\n'
)
tofl = np.zeros(len(weights_tofl[j]))
secsegclbgrad = np.zeros(len(weights_tofl[j]))
thrust = np.zeros(len(weights_tofl[j]))
l_over_d = np.zeros(len(weights_tofl[j]))
l_over_d_v2 = np.zeros(len(weights_tofl[j]))
asymmetry_drag_coefficient = np.zeros(len(weights_tofl[j]))
windmilling_drag_coefficient = np.zeros(len(weights_tofl[j]))
clv2 = np.zeros(len(weights_tofl[j]))
cdv2 = np.zeros(len(weights_tofl[j]))
secsegclbgrad_corrected = np.zeros(len(weights_tofl[j]))
CLmax_ind = 0
# configs.takeoff.maximum_lift_coefficient = maximum_lift_coefficient[CLmax_ind]
configs.takeoff.wings[
'main_wing'].flaps.angle = flaps[CLmax_ind] * Units.deg
configs.takeoff.wings[
'main_wing'].slats.angle = slats[CLmax_ind] * Units.deg
for i, TOW in enumerate(weights_tofl[j]):
configs.takeoff.mass_properties.takeoff = TOW * Units.kg
tofl[i], secsegclbgrad[i], thrust[i], l_over_d[i], l_over_d_v2[i], asymmetry_drag_coefficient[i], \
windmilling_drag_coefficient[i], clv2[i], cdv2[i], secsegclbgrad_corrected[
i] = estimate_take_off_field_length(configs.takeoff,
analyses, airport,
clb_grad)
if secsegclbgrad_corrected[i] < 0.024:
# CLmax_ind = CLmax_ind + 1
# if CLmax_ind > 1:
# CLmax_ind = 1
print CLmax_ind, CLmax_ind, CLmax_ind, CLmax_ind, CLmax_ind, CLmax_ind
configs.takeoff.wings[
'main_wing'].flaps.angle = flaps[CLmax_ind] * Units.deg
configs.takeoff.wings[
'main_wing'].slats.angle = slats[CLmax_ind] * Units.deg
tofl[i], secsegclbgrad[i], thrust[i], l_over_d[i], l_over_d_v2[i], asymmetry_drag_coefficient[i], \
windmilling_drag_coefficient[i], clv2[i], cdv2[i], secsegclbgrad_corrected[
i] = estimate_take_off_field_length(configs.takeoff,
analyses, airport,
clb_grad)
fid.write(
'%4.2f %4.4f %4.4f %4.4f %4.4f %4.4f %4.4f %4.4f %4.4f %4.4f \n'
% (tofl[i], secsegclbgrad[i], thrust[i], l_over_d[i],
l_over_d_v2[i], asymmetry_drag_coefficient[i],
windmilling_drag_coefficient[i], clv2[i], cdv2[i],
secsegclbgrad_corrected[i]))
fid.write('\n')
fid.close()
# ---------------------------------------------------------------------------------------
# LANDING FIELD LENGTH
# ---- Inputs
airport.delta_isa = 0
altitude = [0, 6000]
weights_lfl = [[17000, 18000, 19000, 20000, 21000, 22000, 22350],
[17000, 18000, 19000, 20000, 21000, 22000, 22350]]
flaps = [30., 15.]
slats = [0., 0.]
configs.landing.landing_constants = Data()
configs.landing.landing_constants[0] = 250. * 0.25
configs.landing.landing_constants[1] = 0.
configs.landing.landing_constants[2] = 2.485 / 9.81
configs.landing.wings['main_wing'].flaps.angle = flaps[0] * Units.deg
configs.landing.wings['main_wing'].slats.angle = slats[0] * Units.deg
configs.landing.max_lift_coefficient_factor = 1.31
fid = open('LFL.txt', 'w') # Open output file
for j, h in enumerate(altitude):
airport.altitude = h * Units.ft
lfl = np.zeros(len(weights_lfl[j]))
fid.write('Altitude: %4.0f ft \n' % (h))
for i, TOW in enumerate(weights_lfl[j]):
configs.landing.mass_properties.landing = TOW * Units.kg
lfl[i] = estimate_landing_field_length(configs.landing, analyses,
airport)
fid.write('%4.2f \n' % (lfl[i]))
fid.write('\n')
fid.close()
return
