fixing regressions

regression/scripts/VTOL/test_Stopped_Rotor.py

@@ -74,7 +74,7 @@ def main():
 
     # RPM of rotor check during hover
     RPM        = results.segments.climb_1.conditions.propulsion.lift_rotor_rpm[0][0]
-    RPM_true   = 2403.0042142186653
+    RPM_true   = 2403.004214209376
     print(RPM)
     diff_RPM   = np.abs(RPM - RPM_true)
     print('RPM difference')
@@ -266,8 +266,6 @@ def mission_setup(analyses,vehicle):
     segment.process.iterate.conditions.stability     = SUAVE.Methods.skip
     segment.process.finalize.post_process.stability  = SUAVE.Methods.skip
     segment = vehicle.networks.lift_cruise.add_transition_unknowns_and_residuals_to_segment(segment,
-                                                         initial_prop_power_coefficient = 0.2,
-                                                         initial_lift_rotor_power_coefficient = 0.01,
                                                          initial_throttle_lift = 0.9,)
 
     # add to misison

regression/scripts/Vehicles/Tiltrotor.py

@@ -412,6 +412,7 @@ def vehicle_setup():
     prop.design_thrust          = (1.1*Hover_Load)/net.number_of_propeller_engines
     prop.origin                 = [[2.,5.7,0.784]]
     prop.rotation               = -1
+    prop.sol_tolerance          = 1e-4
     prop.symmetry               = True
     prop.variable_pitch         = True 
     prop.airfoil_geometry       =  ['../Vehicles/Airfoils/NACA_4412.txt']

regression/scripts/segments/transition_segment_test.py

@@ -60,10 +60,10 @@ def main():
 
 
     # Truth values
-    departure_throttle_truth          = np.array([0.65161055, 0.65183868, 0.65231038, 0.65255396])
-    transition_1_throttle_truth       = np.array([0.65403001, 0.64894357, 0.52035828, 0.58035213])
-    cruise_throttle_truth             = np.array([0.46376188, 0.46410014, 0.46477841, 0.46511841])
-    transition_y_axis_rotations_truth = np.array([1.36961133, 1.34419493, 1.1039408 , 0.06583135])
+    departure_throttle_truth          = np.array([0.65161054, 0.65183868, 0.65231039, 0.65255397])
+    transition_1_throttle_truth       = np.array([0.65434873, 0.64834806, 0.52075861, 0.58035428])
+    cruise_throttle_truth             = np.array([0.46376169, 0.46409995, 0.4647782 , 0.4651182 ])
+    transition_y_axis_rotations_truth = np.array([1.36961133, 1.34327318, 1.10250854, 0.06580108])
 
     # Store errors 
     error = Data()

trunk/SUAVE/Components/Energy/Converters/Rotor.py

@@ -83,6 +83,7 @@ def __defaults__(self):
         self.vtk_airfoil_points           = 40
         self.induced_power_factor         = 1.48         # accounts for interference effects
         self.profile_drag_coefficient     = .03
+        self.sol_tolerance                = 1e-8
 
         self.use_2d_analysis           = False    # True if rotor is at an angle relative to freestream or nonuniform freestream
         self.nonuniform_freestream     = False

trunk/SUAVE/Methods/Propulsion/Rotor_Wake/Fidelity_Zero/fidelity_zero_wake_convergence.py

@@ -48,9 +48,9 @@ def fidelity_zero_wake_convergence(wake,rotor,wake_inputs):
     if wake_inputs.use_2d_analysis:
         PSI    = np.ones((ctrl_pts,Nr,Na))
     else:
-        PSI     = np.ones((ctrl_pts,Nr))
+        PSI    = np.ones((ctrl_pts,Nr))
 
-    PSI_final,infodict,ier,msg = sp.optimize.fsolve(iteration,PSI,args=(wake_inputs,rotor),full_output = 1)
+    PSI_final,infodict,ier,msg = sp.optimize.fsolve(iteration,PSI,args=(wake_inputs,rotor),xtol=rotor.sol_tolerance,full_output = 1,band=(1,0))
 
     if ier!=1:
         print("Rotor BEVW did not converge to a solution (Stall)")