@@ -90,6 +90,7 @@ Display a plot at specified DPI.
9090- `dpi`: Dots per inch for the figure (default: 130)
9191"""
9292function VortexStepMethod. show_plot (fig; dpi= 130 )
93+ fig. set_dpi (dpi)
9394 plt. display (fig)
9495end
9596
@@ -183,7 +184,6 @@ function create_geometry_plot(body_aero::BodyAerodynamics, title, view_elevation
183184 end
184185
185186 # Extract geometric data
186- corner_points = [panel. corner_points for panel in panels]
187187 control_points = [panel. control_point for panel in panels]
188188 aero_centers = [panel. aero_center for panel in panels]
189189
@@ -239,7 +239,6 @@ function create_geometry_plot(body_aero::BodyAerodynamics, title, view_elevation
239239 plot_line_segment! (ax, [va_vector_begin, va_vector_end], :lightblue , " va" )
240240
241241 # Add legends for the first occurrence of each label
242- handles, labels = ax. get_legend_handles_labels ()
243242 # by_label = Dict(zip(labels, handles))
244243 # ax.legend(values(by_label), keys(by_label), bbox_to_anchor=(0, 0, 1.1, 1))
245244
@@ -520,6 +519,8 @@ function generate_polar_data(
520519 v_a= 10.0 ,
521520 use_latex= false
522521)
522+ _ = use_latex
523+
523524 n_panels = length (body_aero. panels)
524525 n_angles = length (angle_range)
525526
@@ -533,9 +534,6 @@ function generate_polar_data(
533534 cs_distribution = zeros (n_angles, n_panels)
534535 reynolds_number = zeros (n_angles)
535536
536- # Previous gamma for initialization
537- gamma = nothing
538-
539537 for (i, angle_i) in enumerate (angle_range)
540538 # Set angle based on type
541539 if angle_type == " angle_of_attack"
@@ -569,9 +567,6 @@ function generate_polar_data(
569567 cd_distribution[i, :] = results[" cd_distribution" ]
570568 cs_distribution[i, :] = results[" cs_distribution" ]
571569 reynolds_number[i] = results[" Rey" ]
572-
573- # Store gamma for next iteration
574- gamma = gamma_distribution[i, :]
575570 end
576571
577572 polar_data = [
@@ -896,7 +891,7 @@ function VortexStepMethod.plot_polar_data(body_aero::BodyAerodynamics;
896891 use_tex = false
897892 )
898893 if body_aero. panels[1 ]. aero_model == POLAR_MATRICES
899- set_plot_style ()
894+ set_plot_style (; use_tex )
900895
901896 # Create figure with subplots
902897 fig = plt. figure (figsize= (15 , 6 ))
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