From e7747ce01066e28efe4a97a1dab91a385f63147d Mon Sep 17 00:00:00 2001
From: camUrban <camerongurban@gmail.com>
Date: Tue, 3 Dec 2024 22:58:56 -0500
Subject: [PATCH] I started making an example file with Daniobot's tail
 geometry

---
 .idea/dictionaries/camer.xml |   1 +
 daniobot/daniobot.py         | 135 +++++++++++++++++++++++++++++++++++
 2 files changed, 136 insertions(+)
 create mode 100644 daniobot/daniobot.py

diff --git a/.idea/dictionaries/camer.xml b/.idea/dictionaries/camer.xml
index c9686354..319f66f4 100644
--- a/.idea/dictionaries/camer.xml
+++ b/.idea/dictionaries/camer.xml
@@ -32,6 +32,7 @@
       <w>cosspace</w>
       <w>curtiss</w>
       <w>customspace</w>
+      <w>daniobot</w>
       <w>davissm</w>
       <w>dbln</w>
       <w>dfvlr</w>
diff --git a/daniobot/daniobot.py b/daniobot/daniobot.py
new file mode 100644
index 00000000..8090bce3
--- /dev/null
+++ b/daniobot/daniobot.py
@@ -0,0 +1,135 @@
+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=2.00e-2,
+                    airfoil=ps.geometry.Airfoil(
+                        name="naca0012",
+                    ),
+                ),
+                ps.geometry.WingCrossSection(
+                    num_spanwise_panels=8,
+                    spanwise_spacing="cosine",
+                    y_le=0.50e-2,
+                    chord=2.00e-2,
+                    airfoil=ps.geometry.Airfoil(
+                        name="naca0012",
+                    ),
+                ),
+                ps.geometry.WingCrossSection(
+                    x_le=0.50e-2,
+                    y_le=1.00e-2,
+                    chord=1.50e-2,
+                    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=1.0,
+    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=1.0,
+    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=1.0,
+    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,
+    ],
+)
+
+daniobot_movement = ps.movement.AirplaneMovement(
+    base_airplane=daniobot,
+    wing_movements=[tail_movement],
+)
+
+del tail_movement
+
+operating_point = ps.operating_point.OperatingPoint(
+    density=997,
+    beta=0.0,
+    velocity=0.01,
+    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,
+    num_cycles=5,
+)
+
+del daniobot_movement
+del operating_point_movement
+
+problem = ps.problems.UnsteadyProblem(
+    movement=movement,
+)
+
+del movement
+
+solver = ps.unsteady_ring_vortex_lattice_method.UnsteadyRingVortexLatticeMethodSolver(
+    unsteady_problem=problem,
+)
+
+del problem
+
+solver.run(
+    prescribed_wake=False,
+    calculate_streamlines=False,
+)
+
+ps.output.animate(
+    unsteady_solver=solver,
+    scalar_type="induced drag",
+    show_wake_vortices=True,
+    save=False,
+)
+
+ps.output.draw(
+    solver=solver,
+    scalar_type="induced drag",
+    show_wake_vortices=True,
+    save=False,
+)