Update README.md

ufechner7 · ufechner7 · commit 7252c0a98c03 · 2025-02-26T20:26:59.000+01:00
diff --git a/README.md b/README.md
@@ -97,7 +97,7 @@ alpha_deg = 30.0       # Angle of attack [degrees]
 alpha = deg2rad(alpha_deg)
 
 # Step 2: Create wing geometry with linear panel distribution
-wing = Wing(n_panels, spanwise_panel_distribution="linear")
+wing = Wing(n_panels, spanwise_panel_distribution=LINEAR)
 
 # Add wing sections - defining only tip sections with inviscid airfoil model
 add_section!(wing, 
diff --git a/docs/src/index.md b/docs/src/index.md
@@ -98,7 +98,7 @@ alpha_deg = 30.0       # Angle of attack [degrees]
 alpha = deg2rad(alpha_deg)
 
 # Step 2: Create wing geometry with linear panel distribution
-wing = Wing(n_panels, spanwise_panel_distribution="linear")
+wing = Wing(n_panels, spanwise_panel_distribution=LINEAR)
 
 # Add wing sections - defining only tip sections with inviscid airfoil model
 add_section!(wing, 
