I updated the Daniobot example and added a convergence example.

daniobot/daniobot.py

@@ -1,5 +1,3 @@
-import math
-
 import pterasoftware as ps
 
 daniobot = ps.geometry.Airplane(
@@ -14,31 +12,22 @@
             y_le=0.0,
             z_le=0.0,
             symmetric=True,
-            unit_chordwise_vector=[1 / math.sqrt(2), 0, 1 / math.sqrt(2)],
             num_chordwise_panels=16,
             chordwise_spacing="uniform",
             wing_cross_sections=[
                 ps.geometry.WingCrossSection(
-                    num_spanwise_panels=8,
+                    num_spanwise_panels=4,
                     spanwise_spacing="cosine",
-                    chord=7.684e-3,
+                    chord=7e-3,
                     airfoil=ps.geometry.Airfoil(
                         name="naca0012",
                     ),
                 ),
                 ps.geometry.WingCrossSection(
-                    num_spanwise_panels=8,
+                    num_spanwise_panels=4,
                     spanwise_spacing="cosine",
-                    y_le=1.568e-3,
-                    chord=7.294e-3,
-                    airfoil=ps.geometry.Airfoil(
-                        name="naca0012",
-                    ),
-                ),
-                ps.geometry.WingCrossSection(
-                    x_le=3.601e-3,
-                    y_le=3.128e-3,
-                    chord=2.70e-3,
+                    y_le=3e-3,
+                    chord=7e-3,
                     airfoil=ps.geometry.Airfoil(
                         name="naca0012",
                     ),
@@ -55,34 +44,30 @@
     pitching_spacing="sine",
 )
 
-tail_mid_wing_cross_section_movement = ps.movement.WingCrossSectionMovement(
-    base_wing_cross_section=daniobot.wings[0].wing_cross_sections[1],
-    # pitching_amplitude=15.0,
-    # pitching_period=1 / 8,
-    # pitching_spacing="sine",
-)
-
 tail_tip_wing_cross_section_movement = ps.movement.WingCrossSectionMovement(
-    base_wing_cross_section=daniobot.wings[0].wing_cross_sections[2],
-    # pitching_amplitude=15.0,
-    # pitching_period=1 / 8,
-    # pitching_spacing="sine",
+    base_wing_cross_section=daniobot.wings[0].wing_cross_sections[1],
+    pitching_amplitude=15.0,
+    pitching_period=1 / 8,
+    pitching_spacing="sine",
 )
 
 tail_movement = ps.movement.WingMovement(
     base_wing=daniobot.wings[0],
     wing_cross_sections_movements=[
         tail_root_wing_cross_section_movement,
-        tail_mid_wing_cross_section_movement,
         tail_tip_wing_cross_section_movement,
     ],
 )
 
+del tail_root_wing_cross_section_movement
+del tail_tip_wing_cross_section_movement
+
 daniobot_movement = ps.movement.AirplaneMovement(
     base_airplane=daniobot,
     wing_movements=[tail_movement],
 )
 
+del daniobot
 del tail_movement
 
 operating_point = ps.operating_point.OperatingPoint(
@@ -100,8 +85,8 @@
 movement = ps.movement.Movement(
     airplane_movements=[daniobot_movement],
     operating_point_movement=operating_point_movement,
-    delta_time=1 / 8 / 20,
-    num_cycles=1,
+    delta_time=1 / 8 / 30,
+    num_cycles=5,
 )
 
 del daniobot_movement
@@ -120,7 +105,7 @@
 del problem
 
 solver.run(
-    prescribed_wake=True,
+    prescribed_wake=False,
     calculate_streamlines=False,
 )
 
@@ -145,3 +130,7 @@
     show=True,
     save=False,
 )
+
+ps.output.print_unsteady_results(
+    unsteady_solver=solver,
+)

daniobot/daniobot_converge.py

@@ -0,0 +1,154 @@
+import pterasoftware as ps
+
+daniobot = ps.geometry.Airplane(
+    name="Daniobot",
+    x_ref=0.0,
+    y_ref=0.0,
+    z_ref=0.0,
+    wings=[
+        ps.geometry.Wing(
+            name="Tail",
+            x_le=0.0,
+            y_le=0.0,
+            z_le=0.0,
+            symmetric=True,
+            num_chordwise_panels=16,
+            chordwise_spacing="uniform",
+            wing_cross_sections=[
+                ps.geometry.WingCrossSection(
+                    num_spanwise_panels=8,
+                    spanwise_spacing="cosine",
+                    chord=7e-3,
+                    airfoil=ps.geometry.Airfoil(
+                        name="naca0012",
+                    ),
+                ),
+                ps.geometry.WingCrossSection(
+                    num_spanwise_panels=8,
+                    spanwise_spacing="cosine",
+                    y_le=3e-3,
+                    chord=7e-3,
+                    airfoil=ps.geometry.Airfoil(
+                        name="naca0012",
+                    ),
+                ),
+            ],
+        ),
+    ],
+)
+
+tail_root_wing_cross_section_movement = ps.movement.WingCrossSectionMovement(
+    base_wing_cross_section=daniobot.wings[0].wing_cross_sections[0],
+    pitching_amplitude=15.0,
+    pitching_period=1 / 8,
+    pitching_spacing="sine",
+)
+
+tail_tip_wing_cross_section_movement = ps.movement.WingCrossSectionMovement(
+    base_wing_cross_section=daniobot.wings[0].wing_cross_sections[1],
+    pitching_amplitude=15.0,
+    pitching_period=1 / 8,
+    pitching_spacing="sine",
+)
+
+tail_movement = ps.movement.WingMovement(
+    base_wing=daniobot.wings[0],
+    wing_cross_sections_movements=[
+        tail_root_wing_cross_section_movement,
+        tail_tip_wing_cross_section_movement,
+    ],
+)
+
+del tail_root_wing_cross_section_movement
+del tail_tip_wing_cross_section_movement
+
+daniobot_movement = ps.movement.AirplaneMovement(
+    base_airplane=daniobot,
+    wing_movements=[tail_movement],
+)
+
+del daniobot
+del tail_movement
+
+operating_point = ps.operating_point.OperatingPoint(
+    density=997,
+    beta=0.0,
+    velocity=10e-3,
+    alpha=0,
+    nu=1.00e-6,
+)
+
+operating_point_movement = ps.movement.OperatingPointMovement(
+    base_operating_point=operating_point,
+)
+
+movement = ps.movement.Movement(
+    airplane_movements=[daniobot_movement],
+    operating_point_movement=operating_point_movement,
+    delta_time=None,
+    num_cycles=None,
+)
+
+del daniobot_movement
+del operating_point_movement
+
+problem = ps.problems.UnsteadyProblem(
+    movement=movement,
+)
+
+ps.convergence.analyze_unsteady_convergence(
+    ref_problem=problem,
+    prescribed_wake=True,
+    free_wake=True,
+    num_cycles_bounds=(5 - 2, 5 + 2),
+    panel_aspect_ratio_bounds=(4, 1),
+    num_chordwise_panels_bounds=(16 - 2, 16 + 2),
+    convergence_criteria=5,
+    coefficient_mask=[True, False, False, False, False, False],
+)
+
+# INFO:convergence:The analysis found a converged mesh:
+# INFO:convergence:	Wake type: prescribed
+# INFO:convergence:	Cycles: 6
+# INFO:convergence:	Panel aspect ratio: 4
+# INFO:convergence:	Chordwise panels: 15
+# INFO:convergence:	Iteration time: 0.207 s
+
+# del movement
+#
+# solver = ps.unsteady_ring_vortex_lattice_method.UnsteadyRingVortexLatticeMethodSolver(
+#     unsteady_problem=problem,
+# )
+#
+# del problem
+#
+# solver.run(
+#     prescribed_wake=True,
+#     calculate_streamlines=False,
+# )
+#
+# # ps.output.animate(
+# #     unsteady_solver=solver,
+# #     scalar_type="induced drag",
+# #     show_wake_vortices=True,
+# #     parallel_projection=True,
+# #     save=True,
+# # )
+#
+# ps.output.draw(
+#     solver=solver,
+#     scalar_type="induced drag",
+#     show_wake_vortices=True,
+#     parallel_projection=True,
+#     save=True,
+# )
+#
+# ps.output.plot_results_versus_time(
+#     unsteady_solver=solver,
+#     show=True,
+#     save=False,
+# )
+#
+# ps.output.print_unsteady_results(
+#     unsteady_solver=solver,
+# )