some code cleanup for Regional_Jet_Optimization/

Author: jmvegh

Regional_Jet_Optimization/Optimize.py

@@ -133,7 +133,7 @@ def setup():
     return nexus
 
 def variable_sweep(problem):    
-    number_of_points=20
+    number_of_points=5
     outputs=carpet_plot(problem, number_of_points, 0, 0)  #run carpet plot, suppressing default plots
     inputs =outputs.inputs
     objective=outputs.objective
@@ -153,7 +153,7 @@ def variable_sweep(problem):
     plt.xlabel('wing area (m^2)')
     plt.ylabel('cruise_altitude (km)')
 
-     
+    '''
     #now plot optimization path (note that these data points were post-processed into a plottable format)
     wing_1  = [95          ,	95.00000149 ,	95          ,	95          ,	95.00000149 ,	95          ,	95          ,	95.00000149 ,	95          ,	106.674165  ,	106.6741665 ,	106.674165  ,	106.674165  ,	106.6741665 ,	106.674165  ,	106.674165  ,	106.6741665 ,	106.674165  ,	105.6274294 ,	105.6274309 ,	105.6274294 ,	105.6274294 ,	105.6274309 ,	105.6274294 ,	105.6274294 ,	105.6274309 ,	105.6274294 ,	106.9084316 ,	106.9084331 ,	106.9084316 ,	106.9084316 ,	106.9084331 ,	106.9084316 ,	106.9084316 ,	106.9084331 ,	106.9084316 ,	110.520489  ,	110.5204905 ,	110.520489  ,	110.520489  ,	110.5204905 ,	110.520489  ,	110.520489  ,	110.5204905 ,	110.520489  ,	113.2166831 ,	113.2166845 ,	113.2166831 ,	113.2166831 ,	113.2166845 ,	113.2166831 ,	113.2166831 ,	113.2166845 ,	113.2166831 ,	114.1649262 ,	114.1649277 ,	114.1649262 ,	114.1649262 ,	114.1649277 ,	114.1649262 ,	114.1649262 ,	114.1649277 ,	114.1649262 ,	114.2149828]
     alt_1   = [11.0              ,	11.0              ,	11.000000149011612,	11.0              ,	11.0              ,	11.000000149011612,	11.0              ,	11.0              ,	11.000000149011612,	9.540665954351425 ,	9.540665954351425 ,	9.540666103363037 ,	9.540665954351425 ,	9.540665954351425 ,	9.540666103363037 ,	9.540665954351425 ,	9.540665954351425 ,	9.540666103363037 ,	10.023015652305284,	10.023015652305284,	10.023015801316896,	10.023015652305284,	10.023015652305284,	10.023015801316896,	10.023015652305284,	10.023015652305284,	10.023015801316896,	10.190994033521863,	10.190994033521863,	10.190994182533474,	10.190994033521863,	10.190994033521863,	10.190994182533474,	10.190994033521863,	10.190994033521863,	10.190994182533474,	10.440582829327589,	10.440582829327589,	10.4405829783392  ,	10.440582829327589,	10.440582829327589,	10.4405829783392  ,	10.440582829327589,	10.440582829327589,	10.4405829783392  ,	10.536514606250261,	10.536514606250261,	10.536514755261873,	10.536514606250261,	10.536514606250261,	10.536514755261873,	10.536514606250261,	10.536514606250261,	10.536514755261873,	10.535957839878783,	10.535957839878783,	10.535957988890395,	10.535957839878783,	10.535957839878783,	10.535957988890395,	10.535957839878783,	10.535957839878783,	10.535957988890395,	10.52829047]
@@ -168,7 +168,7 @@ def variable_sweep(problem):
     opt_2   = plt.plot(wing_2, alt_2, 'k--', label='optimization path 2')
     init_2  = plt.plot(wing_2[0], alt_2[0], 'ko', label= 'initial points')
     final_2 = plt.plot(wing_2[-1], alt_2[-1], 'kx', label= 'final points')
-    
+    '''
     plt.legend(loc='upper left')  
     plt.show()    
 

Regional_Jet_Optimization/Procedure.py

@@ -105,6 +105,31 @@ def simple_sizing(nexus):
     configs=nexus.vehicle_configurations
     base=configs.base
 
+    #find conditions
+    air_speed   = nexus.missions.base.segments['cruise'].air_speed 
+    altitude    = nexus.missions.base.segments['climb_5'].altitude_end
+    atmosphere  = SUAVE.Analyses.Atmospheric.US_Standard_1976()
+    
+    freestream  = atmosphere.compute_values(altitude)
+    freestream0 = atmosphere.compute_values(6000.*Units.ft)  #cabin altitude
+    
+    
+    diff_pressure         = np.max(freestream0.pressure-freestream.pressure,0)
+    fuselage              = base.fuselages['fuselage']
+    fuselage.differential_pressure = diff_pressure 
+    
+    #now size engine
+    mach_number        = air_speed/freestream.speed_of_sound
+    
+    #now add to freestream data object
+    freestream.velocity    = air_speed
+    freestream.mach_number = mach_number
+    freestream.gravity     = 9.81
+    
+    conditions             = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()   #assign conditions in form for propulsor sizing
+    conditions.freestream  = freestream
+    
+    
 
     for config in configs:
         config.wings.horizontal_stabilizer.areas.reference = (26.0/92.0)*config.wings.main_wing.areas.reference
@@ -118,31 +143,9 @@ def simple_sizing(nexus):
 
 
 
-        air_speed   = nexus.missions.base.segments['cruise'].air_speed 
-        altitude    = nexus.missions.base.segments['climb_5'].altitude_end
-        atmosphere  = SUAVE.Analyses.Atmospheric.US_Standard_1976()
-        
-        freestream  = atmosphere.compute_values(altitude)
-        freestream0 = atmosphere.compute_values(6000.*Units.ft)  #cabin altitude
-    
-        fuselage              = base.fuselages['fuselage']
-        diff_pressure         = np.max(freestream0.pressure-freestream.pressure,0)
-        
+        fuselage              = config.fuselages['fuselage']
         fuselage.differential_pressure = diff_pressure 
 
-        #now size engine
-        mach_number        = air_speed/freestream.speed_of_sound
-        
-        #now add to freestream data object
-        freestream.velocity    = air_speed
-        freestream.mach_number = mach_number
-        freestream.gravity     = 9.81
-        
-        conditions             = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()   #assign conditions in form for propulsor sizing
-        conditions.freestream  = freestream
-    
-        
-        
         turbofan_sizing(config.propulsors['turbofan'], mach_number, altitude)
         compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
         # diff the new data