Small change to README (#1)

- Small change to README (434caaa468530d2822e382bddd67bc641f16885f)


Co-authored-by: Anna Ivagnes <aivagnes@users.noreply.huggingface.co>

README.md

@@ -52,7 +52,7 @@ configs:
 
 ## Dataset Description
 
-This dataset contains transonic flow simulations around an airfoil, focusing on internal flow field quantities with varying Mach number.
+This dataset contains transonic flow simulations around an airfoil, focusing on internal flow field quantities with varying angle of attack.
 
 ### Dataset Summary
 
@@ -66,7 +66,7 @@ The dataset consists of three configurations:
 
 - **geometry**: Internal domain node coordinates
 - **snapshots**: Flow field solutions in the domain
-- **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:
 - `velocity`: Velocity magnitude field in the internal domain (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 simulations capture the complex flow phenomena in the transonic regime, including shock waves and expansion regions.
+The dataset was generated using computational fluid dynamics simulations of the Euler equations for compressible transonic flow around an airfoil. The simulations capture the complex flow phenomena in the transonic regime, including shock waves and expansion regions.
 
 ### Preprocessing
 
@@ -115,12 +115,12 @@ ds_params = load_dataset("SISSAmathLab/airfoil-transonic-internal", 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, 6))
 plt.scatter(pts_x, pts_y, c=pressure, cmap='RdBu_r', s=1, alpha=0.6)
 plt.colorbar(label='Pressure')
-plt.title(f'Airfoil Flow Field (Mach={mach_number:.2f})')
+plt.title(f'Airfoil Flow Field (angle of attack={angle_of_attack:.2f})')
 plt.xlabel('x')
 plt.ylabel('y')
 plt.axis('equal')