Add example

Author: ufechner7

data/vsm_settings.yaml

@@ -15,12 +15,6 @@ wings:
       spanwise_panel_distribution: LINEAR
       spanwise_direction: [0.0, 1.0, 0.0]
       remove_nan: true
-    - name: tail
-      n_panels: 20
-      n_groups: 20
-      spanwise_panel_distribution: COSINE
-      spanwise_direction: [0.0, 1.1, 0.0]
-      remove_nan: false
 solver_settings:
     aerodynamic_model_type: VSM
     max_iterations: 1000

data/vsm_settings_dual.yaml

@@ -0,0 +1,26 @@
+Model:
+    VSM: Vortex Step Method
+    LLT: Lifting Line Theory
+PanelDistribution:
+   LINEAR:             Linear distribution
+   COSINE:             Cosine distribution
+   COSINE_VAN_GARREL:  van Garrel cosine distribution
+   SPLIT_PROVIDED:     Split provided sections
+   UNCHANGED:          Keep original sections
+
+wings:
+    - name: main_wing
+      n_panels: 40
+      n_groups: 40
+      spanwise_panel_distribution: LINEAR
+      spanwise_direction: [0.0, 1.0, 0.0]
+      remove_nan: true
+    - name: tail
+      n_panels: 20
+      n_groups: 20
+      spanwise_panel_distribution: COSINE
+      spanwise_direction: [0.0, 1.1, 0.0]
+      remove_nan: false
+solver_settings:
+    aerodynamic_model_type: VSM
+    max_iterations: 1000