Small change to README

README.md

@@ -52,7 +52,7 @@ configs:
 
 ## Dataset Description
 
-This dataset contains transonic flow simulations around an airfoil, focusing on boundary (airfoil surface) quantities with varying Mach number.
+This dataset contains transonic flow simulations around an airfoil, focusing on boundary (airfoil surface) quantities with varying angle of attack.
 
 ### Dataset Summary
 
@@ -66,7 +66,7 @@ The dataset consists of three configurations:
 
 - **geometry**: Airfoil surface node coordinates
 - **snapshots**: Aerodynamic field solutions at the boundary
-- **parameters**: Flow condition parameters (Mach number)
+- **parameters**: Flow condition parameters (angle of attack)
 
 ### Data Fields
 
@@ -79,17 +79,17 @@ The dataset consists of three configurations:
 - `wall_shear_stress`: Wall shear stress distribution along the airfoil surface (float64)
 
 #### Parameters Configuration
-- `mach`: Mach number for each simulation (float64)
+- `angle_of_attack`: angle of attack for each simulation (float64)
 
 ### Data Splits
 
-- `default`: Contains all simulations with varying Mach numbers
+- `default`: Contains all simulations with varying angle of attack
 
 ## Dataset Creation
 
 ### Source Data
 
-The dataset was generated using computational fluid dynamics simulations of the Euler or Reynolds-Averaged Navier-Stokes (RANS) equations for compressible transonic flow around an airfoil. The transonic regime is characterized by mixed subsonic and supersonic flow regions, often exhibiting shock waves.
+The dataset was generated using computational fluid dynamics simulations of the Euler equations for compressible transonic flow around an airfoil. The transonic regime is characterized by mixed subsonic and supersonic flow regions, often exhibiting shock waves.
 
 ### Preprocessing
 
@@ -115,12 +115,12 @@ ds_params = load_dataset("SISSAmathLab/airfoil-transonic-boundary", name="parame
 pts_x = np.asarray(ds_geom['default']['node_coordinates_x']).flatten()
 pts_y = np.asarray(ds_geom['default']['node_coordinates_y']).flatten()
 pressure = ds_data['default']['pressure'][0]
-mach_number = ds_params['default']['mach'][0]
+angle_of_attack = ds_params['default']['angle_of_attack'][0]
 
 plt.figure(figsize=(12, 4))
 plt.scatter(pts_x, pts_y, c=pressure, cmap='RdBu_r', s=20)
 plt.colorbar(label='Pressure')
-plt.title(f'Airfoil Surface Pressure (Mach={mach_number:.2f})')
+plt.title(f'Airfoil Surface Pressure (angle of attack={angle_of_attack:.2f})')
 plt.xlabel('x')
 plt.ylabel('y')
 plt.axis('equal')