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mclarke2mclarke2
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reverting plot changes
1 parent fe91209 commit 2cceaff

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4 files changed

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-87
lines changed

4 files changed

+686
-87
lines changed

‎tut_concorde.py‎

Lines changed: 116 additions & 21 deletions
Original file line numberDiff line numberDiff line change
@@ -13,7 +13,6 @@
1313

1414
import SUAVE
1515
from SUAVE.Core import Units, Data
16-
from SUAVE.Plots.Mission_Plots import *
1716
from SUAVE.Methods.Propulsion.turbojet_sizing import turbojet_sizing
1817

1918
import numpy as np
@@ -482,26 +481,122 @@ def configs_setup(vehicle):
482481
# Plot Mission
483482
# ----------------------------------------------------------------------
484483

485-
def plot_mission(results):
486-
487-
# Plot Flight Conditions
488-
plot_flight_conditions(results)
489-
490-
# Plot Aerodynamic Forces
491-
plot_aerodynamic_forces(results)
492-
493-
# Plot Aerodynamic Coefficients
494-
plot_aerodynamic_coefficients(results)
495-
496-
# Drag Components
497-
plot_drag_components(results)
498-
499-
# Plot Altitude, sfc, vehicle weight
500-
plot_altitude_sfc_weight(results)
501-
502-
# Plot Velocities
503-
plot_aircraft_velocities(results)
504-
484+
def plot_mission(results,line_style='bo-'):
485+
486+
axis_font = {'fontname':'Arial', 'size':'14'}
487+
488+
# ------------------------------------------------------------------
489+
# Propulsion
490+
# ------------------------------------------------------------------
491+
492+
fig = plt.figure("Propulsion",figsize=(8,6))
493+
for segment in results.segments.values():
494+
495+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
496+
Thrust = segment.conditions.frames.body.thrust_force_vector[:,0] /Units.lbf
497+
eta = segment.conditions.propulsion.throttle[:,0]
498+
499+
axes = fig.add_subplot(2,1,1)
500+
axes.plot( time , Thrust , line_style )
501+
axes.set_ylabel('Thrust (lbf)',axis_font)
502+
axes.grid(True)
503+
504+
axes = fig.add_subplot(2,1,2)
505+
axes.plot( time , eta , line_style )
506+
axes.set_xlabel('Time (min)',axis_font)
507+
axes.set_ylabel('eta (lb/lbf-hr)',axis_font)
508+
axes.grid(True)
509+
510+
# ------------------------------------------------------------------
511+
# Aerodynamics
512+
# ------------------------------------------------------------------
513+
fig = plt.figure("Aerodynamic Coefficients",figsize=(8,10))
514+
for segment in results.segments.values():
515+
516+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
517+
CLift = segment.conditions.aerodynamics.lift_coefficient[:,0]
518+
CDrag = segment.conditions.aerodynamics.drag_coefficient[:,0]
519+
aoa = segment.conditions.aerodynamics.angle_of_attack[:,0] / Units.deg
520+
l_d = CLift/CDrag
521+
522+
axes = fig.add_subplot(3,1,1)
523+
axes.plot( time , CLift , line_style )
524+
axes.set_ylabel('Lift Coefficient',axis_font)
525+
axes.grid(True)
526+
527+
axes = fig.add_subplot(3,1,2)
528+
axes.plot( time , l_d , line_style )
529+
axes.set_ylabel('L/D',axis_font)
530+
axes.grid(True)
531+
532+
axes = fig.add_subplot(3,1,3)
533+
axes.plot( time , aoa , 'ro-' )
534+
axes.set_xlabel('Time (min)',axis_font)
535+
axes.set_ylabel('AOA (deg)',axis_font)
536+
axes.grid(True)
537+
538+
# ------------------------------------------------------------------
539+
# Drag
540+
# ------------------------------------------------------------------
541+
fig = plt.figure("Drag Components",figsize=(8,10))
542+
axes = plt.gca()
543+
for i, segment in enumerate(results.segments.values()):
544+
545+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
546+
drag_breakdown = segment.conditions.aerodynamics.drag_breakdown
547+
cdp = drag_breakdown.parasite.total[:,0]
548+
cdi = drag_breakdown.induced.total[:,0]
549+
cdc = drag_breakdown.compressible.total[:,0]
550+
cdm = drag_breakdown.miscellaneous.total[:,0]
551+
cd = drag_breakdown.total[:,0]
552+
553+
if line_style == 'bo-':
554+
axes.plot( time , cdp , 'ko-', label='CD parasite' )
555+
axes.plot( time , cdi , 'bo-', label='CD induced' )
556+
axes.plot( time , cdc , 'go-', label='CD compressibility' )
557+
axes.plot( time , cdm , 'yo-', label='CD miscellaneous' )
558+
axes.plot( time , cd , 'ro-', label='CD total' )
559+
if i == 0:
560+
axes.legend(loc='upper center')
561+
else:
562+
axes.plot( time , cdp , line_style )
563+
axes.plot( time , cdi , line_style )
564+
axes.plot( time , cdc , line_style )
565+
axes.plot( time , cdm , line_style )
566+
axes.plot( time , cd , line_style )
567+
568+
axes.set_xlabel('Time (min)')
569+
axes.set_ylabel('CD')
570+
axes.grid(True)
571+
572+
# ------------------------------------------------------------------
573+
# Altitude, Vehicle Weight, Mach Number
574+
# ------------------------------------------------------------------
575+
576+
fig = plt.figure("Altitude_sfc_weight",figsize=(8,10))
577+
for segment in results.segments.values():
578+
579+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
580+
mass = segment.conditions.weights.total_mass[:,0] / Units.lb
581+
altitude = segment.conditions.freestream.altitude[:,0] / Units.feet
582+
mach = segment.conditions.freestream.mach_number[:,0]
583+
584+
axes = fig.add_subplot(3,1,1)
585+
axes.plot( time , altitude , line_style )
586+
axes.set_ylabel('Altitude (ft)',axis_font)
587+
axes.grid(True)
588+
589+
axes = fig.add_subplot(3,1,2)
590+
axes.plot( time , mass , 'ro-' )
591+
axes.set_ylabel('Weight (lb)',axis_font)
592+
axes.grid(True)
593+
594+
axes = fig.add_subplot(3,1,3)
595+
axes.plot( time , mach , line_style )
596+
axes.set_xlabel('Time (min)',axis_font)
597+
axes.set_ylabel('Mach Number',axis_font)
598+
axes.grid(True)
599+
505600
return
506601

507602
def simple_sizing(configs):

‎tut_mission_B737.py‎

Lines changed: 163 additions & 20 deletions
Original file line numberDiff line numberDiff line change
@@ -13,8 +13,7 @@
1313

1414
# SUAVE Imports
1515
import SUAVE
16-
from SUAVE.Core import Data, Units
17-
from SUAVE.Plots.Mission_Plots import *
16+
from SUAVE.Core import Data, Units
1817
from SUAVE.Methods.Propulsion.turbofan_sizing import turbofan_sizing
1918
from SUAVE.Methods.Geometry.Two_Dimensional.Cross_Section.Propulsion import compute_turbofan_geometry
2019
from SUAVE.Input_Output.Results import print_parasite_drag, \
@@ -823,25 +822,169 @@ def missions_setup(base_mission):
823822
# Plot Mission
824823
# ----------------------------------------------------------------------
825824

826-
def plot_mission(results):
825+
def plot_mission(results,line_style='bo-'):
827826

828-
# Plot Flight Conditions
829-
plot_flight_conditions(results)
830-
831-
# Plot Aerodynamic Forces
832-
plot_aerodynamic_forces(results)
833-
834-
# Plot Aerodynamic Coefficients
835-
plot_aerodynamic_coefficients(results)
836-
837-
# Drag Components
838-
plot_drag_components(results)
839-
840-
# Plot Altitude, sfc, vehicle weight
841-
plot_altitude_sfc_weight(results)
842-
843-
# Plot Velocities
844-
plot_aircraft_velocities(results)
827+
axis_font = {'fontname':'Arial', 'size':'14'}
828+
829+
# ------------------------------------------------------------------
830+
# Aerodynamics
831+
# ------------------------------------------------------------------
832+
833+
834+
fig = plt.figure("Aerodynamic Forces",figsize=(8,6))
835+
for segment in results.segments.values():
836+
837+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
838+
Thrust = segment.conditions.frames.body.thrust_force_vector[:,0] / Units.lbf
839+
eta = segment.conditions.propulsion.throttle[:,0]
840+
841+
axes = fig.add_subplot(2,1,1)
842+
axes.plot( time , Thrust , line_style )
843+
axes.set_ylabel('Thrust (lbf)',axis_font)
844+
axes.grid(True)
845+
846+
axes = fig.add_subplot(2,1,2)
847+
axes.plot( time , eta , line_style )
848+
axes.set_xlabel('Time (min)',axis_font)
849+
axes.set_ylabel('Throttle',axis_font)
850+
axes.grid(True)
851+
852+
plt.savefig("B737_engine.pdf")
853+
plt.savefig("B737_engine.png")
854+
855+
# ------------------------------------------------------------------
856+
# Aerodynamics 2
857+
# ------------------------------------------------------------------
858+
fig = plt.figure("Aerodynamic Coefficients",figsize=(8,10))
859+
for segment in results.segments.values():
860+
861+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
862+
CLift = segment.conditions.aerodynamics.lift_coefficient[:,0]
863+
CDrag = segment.conditions.aerodynamics.drag_coefficient[:,0]
864+
aoa = segment.conditions.aerodynamics.angle_of_attack[:,0] / Units.deg
865+
l_d = CLift/CDrag
866+
867+
axes = fig.add_subplot(3,1,1)
868+
axes.plot( time , CLift , line_style )
869+
axes.set_ylabel('Lift Coefficient',axis_font)
870+
axes.grid(True)
871+
872+
axes = fig.add_subplot(3,1,2)
873+
axes.plot( time , l_d , line_style )
874+
axes.set_ylabel('L/D',axis_font)
875+
axes.grid(True)
876+
877+
axes = fig.add_subplot(3,1,3)
878+
axes.plot( time , aoa , 'ro-' )
879+
axes.set_xlabel('Time (min)',axis_font)
880+
axes.set_ylabel('AOA (deg)',axis_font)
881+
axes.grid(True)
882+
883+
plt.savefig("B737_aero.pdf")
884+
plt.savefig("B737_aero.png")
885+
886+
# ------------------------------------------------------------------
887+
# Aerodynamics 2
888+
# ------------------------------------------------------------------
889+
fig = plt.figure("Drag Components",figsize=(8,10))
890+
axes = plt.gca()
891+
for i, segment in enumerate(results.segments.values()):
892+
893+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
894+
drag_breakdown = segment.conditions.aerodynamics.drag_breakdown
895+
cdp = drag_breakdown.parasite.total[:,0]
896+
cdi = drag_breakdown.induced.total[:,0]
897+
cdc = drag_breakdown.compressible.total[:,0]
898+
cdm = drag_breakdown.miscellaneous.total[:,0]
899+
cd = drag_breakdown.total[:,0]
900+
901+
if line_style == 'bo-':
902+
axes.plot( time , cdp , 'ko-', label='CD parasite' )
903+
axes.plot( time , cdi , 'bo-', label='CD induced' )
904+
axes.plot( time , cdc , 'go-', label='CD compressibility' )
905+
axes.plot( time , cdm , 'yo-', label='CD miscellaneous' )
906+
axes.plot( time , cd , 'ro-', label='CD total' )
907+
if i == 0:
908+
axes.legend(loc='upper center')
909+
else:
910+
axes.plot( time , cdp , line_style )
911+
axes.plot( time , cdi , line_style )
912+
axes.plot( time , cdc , line_style )
913+
axes.plot( time , cdm , line_style )
914+
axes.plot( time , cd , line_style )
915+
916+
axes.set_xlabel('Time (min)')
917+
axes.set_ylabel('CD')
918+
axes.grid(True)
919+
plt.savefig("B737_drag.pdf")
920+
plt.savefig("B737_drag.png")
921+
922+
# ------------------------------------------------------------------
923+
# Altitude, sfc, vehicle weight
924+
# ------------------------------------------------------------------
925+
926+
fig = plt.figure("Altitude_sfc_weight",figsize=(8,10))
927+
for segment in results.segments.values():
928+
929+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
930+
aoa = segment.conditions.aerodynamics.angle_of_attack[:,0] / Units.deg
931+
mass = segment.conditions.weights.total_mass[:,0] / Units.lb
932+
altitude = segment.conditions.freestream.altitude[:,0] / Units.ft
933+
mdot = segment.conditions.weights.vehicle_mass_rate[:,0]
934+
thrust = segment.conditions.frames.body.thrust_force_vector[:,0]
935+
sfc = (mdot / Units.lb) / (thrust /Units.lbf) * Units.hr
936+
937+
axes = fig.add_subplot(3,1,1)
938+
axes.plot( time , altitude , line_style )
939+
axes.set_ylabel('Altitude (ft)',axis_font)
940+
axes.grid(True)
941+
942+
axes = fig.add_subplot(3,1,3)
943+
axes.plot( time , sfc , line_style )
944+
axes.set_xlabel('Time (min)',axis_font)
945+
axes.set_ylabel('sfc (lb/lbf-hr)',axis_font)
946+
axes.grid(True)
947+
948+
axes = fig.add_subplot(3,1,2)
949+
axes.plot( time , mass , 'ro-' )
950+
axes.set_ylabel('Weight (lb)',axis_font)
951+
axes.grid(True)
952+
953+
plt.savefig("B737_mission.pdf")
954+
plt.savefig("B737_mission.png")
955+
956+
# ------------------------------------------------------------------
957+
# Velocities
958+
# ------------------------------------------------------------------
959+
fig = plt.figure("Velocities",figsize=(8,10))
960+
for segment in results.segments.values():
961+
962+
time = segment.conditions.frames.inertial.time[:,0] / Units.min
963+
Lift = -segment.conditions.frames.wind.lift_force_vector[:,2]
964+
Drag = -segment.conditions.frames.wind.drag_force_vector[:,0] / Units.lbf
965+
Thrust = segment.conditions.frames.body.thrust_force_vector[:,0] / Units.lb
966+
velocity = segment.conditions.freestream.velocity[:,0]
967+
pressure = segment.conditions.freestream.pressure[:,0]
968+
density = segment.conditions.freestream.density[:,0]
969+
EAS = velocity * np.sqrt(density/1.225)
970+
mach = segment.conditions.freestream.mach_number[:,0]
971+
972+
axes = fig.add_subplot(3,1,1)
973+
axes.plot( time , velocity / Units.kts, line_style )
974+
axes.set_ylabel('velocity (kts)',axis_font)
975+
axes.grid(True)
976+
977+
axes = fig.add_subplot(3,1,2)
978+
axes.plot( time , EAS / Units.kts, line_style )
979+
axes.set_xlabel('Time (min)',axis_font)
980+
axes.set_ylabel('Equivalent Airspeed',axis_font)
981+
axes.grid(True)
982+
983+
axes = fig.add_subplot(3,1,3)
984+
axes.plot( time , mach , line_style )
985+
axes.set_xlabel('Time (min)',axis_font)
986+
axes.set_ylabel('Mach',axis_font)
987+
axes.grid(True)
845988

846989
return
847990

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