Merge 5972e37 into 7c6f1dc

regression/scripts/slipstream/slipstream_test.py

@@ -117,14 +117,14 @@ def regress_1b(results, configs):
     sectional_lift_coeff        = results.segments.cruise.conditions.aerodynamics.lift_breakdown.inviscid_wings_sectional[0]
 
     # lift coefficient and sectional lift coefficient check
-    lift_coefficient_true       = 0.43754861958748476 
-    sectional_lift_coeff_true   = np.array([ 4.40811415e-01,  3.58447605e-01,  3.53758756e-01,  3.05402561e-01,
-                                             5.87270843e-02,  4.49276571e-01,  3.95135393e-01,  3.67274586e-01,
-                                             3.11407447e-01,  5.99032728e-02, -6.60176707e-02, -6.27939836e-02,
-                                            -5.54634997e-02, -4.12681130e-02, -2.43572153e-02, -7.26029863e-02,
-                                            -7.03806008e-02, -6.17510582e-02, -4.64116740e-02, -2.76739451e-02,
-                                             3.50749550e-07,  1.99325526e-09,  1.55733197e-09,  4.01202494e-09,
-                                             2.44844282e-09])
+    lift_coefficient_true       = 0.4375681814886325
+    sectional_lift_coeff_true   = np.array([ 4.39186743e-01,  3.55022830e-01,  3.51363002e-01,  3.03463863e-01,
+                                             5.83427225e-02,  4.49490617e-01,  4.03740726e-01,  3.68481887e-01,
+                                             3.11492900e-01,  6.01164743e-02, -6.61621250e-02, -6.28443495e-02,
+                                            -5.56118594e-02, -4.13996846e-02, -2.44318893e-02, -7.41588710e-02,
+                                            -7.19859998e-02, -6.32091207e-02, -4.77136327e-02, -2.85404276e-02,
+                                             5.13437911e-07,  2.71732702e-09,  2.85037078e-09,  6.96361700e-09,
+                                             4.19821840e-09])
 
     diff_CL = np.abs(lift_coefficient  - lift_coefficient_true)
     print('CL difference')
@@ -208,9 +208,10 @@ def Lift_Rotor_Slipstream(wake_fidelity):
 
 def regress_2(results):
 
-    CL_truth  = 0.41609632
-    CDi_truth = 0.00826812
-    CM_truth  = 0.06915052
+    CL_truth  = 0.41618253
+    CDi_truth = 0.00703032
+    CM_truth  = 0.0690942
+
 
     CL  = results.CL
     CDi = results.CDi

trunk/SUAVE/Analyses/Propulsion/Rotor_Wake_Fidelity_One.py

@@ -8,14 +8,17 @@
 #  Imports
 # ----------------------------------------------------------------------
 from SUAVE.Core import Data
+from SUAVE.Components import Wings
 from SUAVE.Components.Energy.Energy_Component import Energy_Component
 from SUAVE.Analyses.Propulsion.Rotor_Wake_Fidelity_Zero import Rotor_Wake_Fidelity_Zero
 from SUAVE.Methods.Propulsion.Rotor_Wake.Fidelity_One.fidelity_one_wake_convergence import fidelity_one_wake_convergence
 from SUAVE.Methods.Propulsion.Rotor_Wake.Fidelity_One.compute_wake_induced_velocity import compute_wake_induced_velocity
 
+from SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Lift.extract_wing_VD import extract_wing_collocation_points
+
 # package imports
 import copy
-
+import numpy as np
 # ----------------------------------------------------------------------
 #  Generalized Rotor Class
 # ----------------------------------------------------------------------
@@ -153,7 +156,60 @@ def evaluate(self,rotor,wake_inputs,conditions):
 
         return va, vt
 
-    def evaluate_wake_velocities(self,rotor,network,geometry,conditions,VD,num_ctrl_pts):
+    def evaluate_slipstream(self,rotor,geometry,ctrl_pts,wing_instance=None):
+        """
+        Evaluates the velocities induced by the rotor on a specified wing of the vehicle.
+        If no wing instance is specified, uses main wing or last available wing in geometry.
+        
+        Assumptions:
+        None
+
+        Source:
+        N/A
+
+        Inputs:
+           self         - rotor wake
+           rotor        - rotor
+           geometry     - vehicle geometry
+           
+        Outputs:
+           wake_V_ind   - induced velocity from rotor wake at (VD.XC, VD.YC, VD.ZC)
+        
+        Properties Used:
+        None
+        """
+        # Check for wing if wing instance is unspecified
+        if wing_instance == None:
+            nmw = 0
+            # check for main wing
+            for i,wing in enumerate(geometry.wings):
+                if not isinstance(wing,Wings.Main_Wing): continue
+                nmw +=1                
+                wing_instance = wing
+                wing_instance_idx = i
+            if nmw == 1:
+                pass
+            elif nmw>1:
+                print("No wing specified for slipstream analysis. Multiple main wings in vehicle, using the last one.")
+            else:
+                print("No wing specified for slipstream analysis. No main wing defined, using the last wing in vehicle.")
+                wing_instance = wing 
+                wing_instance_idx = i
+
+        # Isolate the VD components corresponding to this wing instance
+        wing_CPs, slipstream_vd_ids = extract_wing_collocation_points(geometry, wing_instance_idx)
+
+        # Evaluate rotor slipstream effect on specified wing instance
+        rot_V_wake_ind = self.evaluate_wake_velocities(rotor, wing_CPs, ctrl_pts)
+
+        # Expand
+        wake_V_ind = np.zeros((ctrl_pts,geometry.vortex_distribution.n_cp,3))
+        wake_V_ind[:,slipstream_vd_ids,:] = rot_V_wake_ind
+
+
+        return wake_V_ind 
+
+    def evaluate_wake_velocities(self,rotor,VD,num_ctrl_pts):
         """
         Links the rotor wake to compute the wake-induced velocities at the vortex distribution
         control points.
@@ -167,9 +223,6 @@ def evaluate_wake_velocities(self,rotor,network,geometry,conditions,VD,num_ctrl_
         Inputs:
            self         - rotor wake
            rotor        - rotor
-           network      - propulsion network
-           geometry     - vehicle geometry
-           conditions   - conditions
            VD           - vortex distribution
            num_ctrl_pts - number of analysis control points
            

trunk/SUAVE/Analyses/Propulsion/Rotor_Wake_Fidelity_Zero.py

@@ -11,10 +11,13 @@
 from SUAVE.Components.Energy.Energy_Component import Energy_Component
 
 
+from SUAVE.Components import Wings
 from SUAVE.Methods.Propulsion.Rotor_Wake.Fidelity_Zero.fidelity_zero_wake_convergence import fidelity_zero_wake_convergence
-from SUAVE.Methods.Propulsion.Rotor_Wake.Fidelity_Zero.compute_bevw_induced_velocity import compute_bevw_induced_velocity
+from SUAVE.Methods.Propulsion.Rotor_Wake.Fidelity_Zero.compute_fidelity_zero_induced_velocity import compute_fidelity_zero_induced_velocity
 
+from SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Lift.extract_wing_VD import extract_wing_collocation_points
 
+import numpy as np
 # ----------------------------------------------------------------------
 #  Generalized Rotor Class
 # ----------------------------------------------------------------------
@@ -88,10 +91,10 @@ def evaluate(self,rotor,wake_inputs,conditions):
 
         return va, vt
 
-    def evaluate_wake_velocities(self,rotor,network,geometry,conditions,VD,num_ctrl_pts):
+    def evaluate_slipstream(self,rotor,geometry,ctrl_pts,wing_instance=None):
         """
-        Links the rotor wake to compute the wake-induced velocities at the vortex distribution
-        control points.
+        Evaluates the velocities induced by the rotor on a specified wing of the vehicle.
+        If no wing instance is specified, uses main wing or last available wing in geometry.
         
         Assumptions:
         None
@@ -102,11 +105,60 @@ def evaluate_wake_velocities(self,rotor,network,geometry,conditions,VD,num_ctrl_
         Inputs:
            self         - rotor wake
            rotor        - rotor
-           network      - propulsion network
            geometry     - vehicle geometry
-           conditions   - conditions
-           VD           - vortex distribution
-           num_ctrl_pts - number of analysis control points
+           
+        Outputs:
+           wake_V_ind   - induced velocity from rotor wake at (VD.XC, VD.YC, VD.ZC)
+        
+        Properties Used:
+        None
+        """
+        # Check for wing if wing instance is unspecified
+        if wing_instance == None:
+            nmw = 0
+            # check for main wing
+            for i,wing in enumerate(geometry.wings):
+                if not isinstance(wing,Wings.Main_Wing): continue
+                nmw +=1                
+                wing_instance = wing
+                wing_instance_idx = i
+            if nmw == 1:
+                pass
+            elif nmw>1:
+                print("No wing specified for slipstream analysis. Multiple main wings in vehicle, using the last one.")
+            else:
+                print("No wing specified for slipstream analysis. No main wing defined, using the last wing in vehicle.")
+                wing_instance = wing 
+                wing_instance_idx = i
+
+        # Isolate the VD components corresponding to this wing instance
+        wing_CPs, slipstream_vd_ids = extract_wing_collocation_points(geometry, wing_instance_idx)
+
+        # Evaluate rotor slipstream effect on specified wing instance
+        rot_V_wake_ind = self.evaluate_wake_velocities(rotor, wing_CPs,ctrl_pts)
+
+        # Expand
+        wake_V_ind = np.zeros((ctrl_pts,geometry.vortex_distribution.n_cp,3))
+        wake_V_ind[:,slipstream_vd_ids,:] = rot_V_wake_ind
+
+
+        return wake_V_ind
+
+    def evaluate_wake_velocities(self,rotor,evaluation_points,ctrl_pts):
+        """
+        Links the rotor wake to compute the wake-induced velocities at the specified
+        evaluation points.
+        
+        Assumptions:
+        None
+
+        Source:
+        N/A
+
+        Inputs:
+           self               - rotor wake
+           rotor              - rotor
+           evaluation_points  - points at which to evaluate the rotor wake-induced velocities 
            
         Outputs:
            prop_V_wake_ind  - induced velocity from rotor wake at (VD.XC, VD.YC, VD.ZC)
@@ -115,14 +167,9 @@ def evaluate_wake_velocities(self,rotor,network,geometry,conditions,VD,num_ctrl_
         None
         """  
 
-        identical_flag = network.identical_propellers
-
-        if network.number_of_propeller_engines == None:
-            pass
-        else:   
-            rots = Data()
-            rots.append(rotor)
-            rot_V_wake_ind = compute_bevw_induced_velocity(rots,geometry,num_ctrl_pts,conditions,identical_flag)  
+        rots = Data()
+        rots.append(rotor)
+        rot_V_wake_ind = compute_fidelity_zero_induced_velocity(evaluation_points,rots,ctrl_pts)  
 
         return rot_V_wake_ind
 

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

@@ -545,7 +545,8 @@ def spin(self,conditions):
                     blade_H_distribution              = rotor_drag_distribution,
                     rotor_drag                        = rotor_drag,
                     rotor_drag_coefficient            = Crd,
-                    figure_of_merit                   = FoM
+                    figure_of_merit                   = FoM,
+                    tip_mach                          = omega * R / conditions.freestream.speed_of_sound
             )
         self.outputs = outputs
 

trunk/SUAVE/Input_Output/VTK/save_prop_vtk.py

@@ -323,7 +323,6 @@ def generate_lofted_propeller_points(prop):
     beta   = prop.twist_distribution
     b      = prop.chord_distribution
     r      = prop.radius_distribution
-    MCA    = prop.mid_chord_alignment
     t      = prop.max_thickness_distribution
     origin = prop.origin
 
@@ -339,7 +338,7 @@ def generate_lofted_propeller_points(prop):
         a_o = prop.start_angle
 
     n_r       = len(b)                               # number radial points
-    n_a_loft  = prop.number_points_around_airfoil    # number points around airfoil
+    n_a_loft  = prop.vtk_airfoil_points              # number points around airfoil
     theta     = np.linspace(0,2*np.pi,num_B+1)[:-1]  # azimuthal stations
 
     # create empty data structure for storing propeller geometries
@@ -350,7 +349,6 @@ def generate_lofted_propeller_points(prop):
     flip_1      = (np.pi/2)
     flip_2      = (np.pi/2)
 
-    MCA_2d = np.repeat(np.atleast_2d(MCA).T,n_a_loft,axis=1)
     b_2d   = np.repeat(np.atleast_2d(b).T  ,n_a_loft,axis=1)
     t_2d   = np.repeat(np.atleast_2d(t).T  ,n_a_loft,axis=1)
     r_2d   = np.repeat(np.atleast_2d(r).T  ,n_a_loft,axis=1)
@@ -378,7 +376,7 @@ def generate_lofted_propeller_points(prop):
         max_t2d = np.repeat(np.atleast_2d(max_t).T ,n_a_loft,axis=1)
 
         airfoil_le_offset = ( - np.repeat(b[:,None], n_a_loft, axis=1)/2 ) # no sweep
-        xp      = (- MCA_2d + xpts*b_2d + airfoil_le_offset)  # x coord of airfoil
+        xp      = (xpts*b_2d + airfoil_le_offset)  # x coord of airfoil
         yp      = r_2d*np.ones_like(xp)                           # radial location
         zp      = zpts*(t_2d/max_t2d)                             # former airfoil y coord
 

trunk/SUAVE/Input_Output/VTK/save_vehicle_vtk.py

@@ -22,7 +22,7 @@
 import numpy as np
 
 ## @ingroup Input_Output-VTK
-def save_vehicle_vtks(vehicle, conditions=None, Results=None, time_step=0,VLM_settings=None, prop_filename="propeller.vtk", rot_filename="rotor.vtk",
+def save_vehicle_vtks(vehicle, conditions=None, Results=Data(), time_step=0,VLM_settings=None, prop_filename="propeller.vtk", rot_filename="rotor.vtk",
                      wake_filename="prop_wake.vtk", wing_vlm_filename="wing_vlm_horseshoes.vtk",wing_filename="wing_vlm.vtk", 
                      fuselage_filename="fuselage.vtk", nacelle_filename="nacelle.vtk", save_loc=None):
     """

trunk/SUAVE/Methods/Aerodynamics/Common/Fidelity_Zero/Lift/compute_RHS_matrix.py

@@ -94,7 +94,7 @@ def compute_RHS_matrix(delta,phi,conditions,settings,geometry,propeller_wake_mod
                 prop_V_wake_ind = np.zeros((num_ctrl_pts,num_eval_pts,3))
 
                 for p in props:
-                    prop_V_wake_ind += p.Wake.evaluate_wake_velocities(p,network,geometry,conditions,VD,num_ctrl_pts)
+                    prop_V_wake_ind += p.Wake.evaluate_slipstream(p,geometry,num_ctrl_pts)
 
 
             if 'lift_rotors' in network.keys(): 
@@ -103,7 +103,7 @@ def compute_RHS_matrix(delta,phi,conditions,settings,geometry,propeller_wake_mod
                 rot_V_wake_ind = np.zeros((num_ctrl_pts,num_eval_pts,3))
 
                 for r in rots:
-                    rot_V_wake_ind += r.Wake.evaluate_wake_velocities(r,network,geometry,conditions,VD,num_ctrl_pts)
+                    rot_V_wake_ind += r.Wake.evaluate_slipstream(r,geometry,num_ctrl_pts)
 
 
             # update the total induced velocity distribution

trunk/SUAVE/Methods/Aerodynamics/Common/Fidelity_Zero/Lift/extract_wing_VD.py

@@ -0,0 +1,54 @@
+## @ingroup Methods-Aerodynamics-Common-Fidelity_Zero-Lift
+# extract_wing_VD.py
+#
+# Created:   Feb 2022, R. Erhard
+# Modified: 
+
+# ----------------------------------------------------------------------
+#  Imports
+# ----------------------------------------------------------------------
+
+# package imports
+from SUAVE.Core import Data
+
+## @ingroup Methods-Aerodynamics-Common-Fidelity_Zero-Lift
+def extract_wing_collocation_points(geometry, wing_instance_idx):
+
+    """ This extracts the collocation points of the vehicle vortex distribution
+    belonging to the specified wing instance index. This is useful for slipstream
+    analysis, where the wake of a propeller is included in the VLM analysis 
+    of a specified wing in the vehicle.
+
+    Source:
+    None
+
+    Inputs:
+    geometry      -    SUAVE vehicle 
+    wing_instance -    wing instance tag
+
+    Outputs:
+    VD_wing   - colocation points of vortex distribution for specified wing
+    ids       - indices in the vortex distribution corresponding to specified wing
+
+    Properties Used:
+    N/A
+    """
+    # unpack vortex distribution properties
+    VD          = geometry.vortex_distribution
+    span_breaks = VD.spanwise_breaks
+    wing        = list(geometry.wings.keys())[wing_instance_idx]
+    sym         = geometry.wings[wing].symmetric
+
+    VD_wing  = Data()       
+    id_start = span_breaks[wing_instance_idx]
+    id_end   = span_breaks[wing_instance_idx + 1 + int(sym)]
+    ids      = range(id_start,id_end)
+
+    VD_wing.XC   = VD.XC[ids]
+    VD_wing.YC   = VD.YC[ids]
+    VD_wing.ZC   = VD.ZC[ids]
+    VD_wing.n_cp = len(VD_wing.XC)
+
+    return VD_wing, ids
+
+

trunk/SUAVE/Methods/Geometry/Two_Dimensional/Cross_Section/Airfoil/import_airfoil_polars.py

@@ -39,8 +39,8 @@ def  import_airfoil_polars(airfoil_polar_files):
     num_polars   = 0
     for i in range(num_airfoils): 
         n_p = len(airfoil_polar_files[i])
-        if n_p < 3:
-            raise AttributeError('Provide three or more airfoil polars to compute surrogate')
+        #if n_p < 3:
+            #raise AttributeError('Provide three or more airfoil polars to compute surrogate')
 
         num_polars = max(num_polars, n_p)       
 

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

@@ -1,5 +1,5 @@
 ## @defgroup Methods-Aerodynamics-Rotor_Wake-Fidelity_Zero
 # Rotor wake methods that are directly specified by analyses.
 
-from .compute_bevw_induced_velocity           import compute_bevw_induced_velocity 
-from .compute_wake_contraction_matrix         import compute_wake_contraction_matrix
+from .compute_fidelity_zero_induced_velocity   import compute_fidelity_zero_induced_velocity 
+from .compute_wake_contraction_matrix          import compute_wake_contraction_matrix