Update README.md

README.md

@@ -48,3 +48,86 @@ configs:
   - split: default
     path: snapshots/default-*
 ---
+# Airfoil Transonic Flow - Internal Domain Dataset
+
+## Dataset Description
+
+This dataset contains transonic flow simulations around an airfoil, focusing on internal flow field quantities with varying Mach number.
+
+### Dataset Summary
+
+The Airfoil Transonic Internal dataset provides numerical simulations of compressible transonic flow around an airfoil profile. The dataset focuses on aerodynamic quantities in the flow field surrounding the airfoil, including pressure and velocity distributions in the computational domain, making it valuable for flow field analysis, aerodynamic research, and machine learning applications in computational fluid dynamics.
+
+## Dataset Structure
+
+### Data Instances
+
+The dataset consists of three configurations:
+
+- **geometry**: Internal domain node coordinates
+- **snapshots**: Flow field solutions in the domain
+- **parameters**: Flow condition parameters (Mach number)
+
+### Data Fields
+
+#### Geometry Configuration
+- `node_coordinates_x`: Sequence of x-coordinates of internal domain nodes (float64)
+- `node_coordinates_y`: Sequence of y-coordinates of internal domain nodes (float64)
+
+#### Snapshots Configuration
+- `pressure`: Pressure field in the internal domain (float64)
+- `velocity`: Velocity magnitude field in the internal domain (float64)
+
+#### Parameters Configuration
+- `mach`: Mach number for each simulation (float64)
+
+### Data Splits
+
+- `default`: Contains all simulations with varying Mach numbers
+
+## 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.
+
+### Preprocessing
+
+Internal domain quantities (flow field around the airfoil, excluding the boundary) are included in this dataset. Solutions are stored as 1D arrays corresponding to the nodes in the computational mesh.
+
+## Usage
+
+```python
+from datasets import load_dataset
+import numpy as np
+import matplotlib.pyplot as plt
+
+# Load geometry
+ds_geom = load_dataset("SISSAmathLab/airfoil-transonic-internal", name="geometry")
+
+# Load snapshots
+ds_data = load_dataset("SISSAmathLab/airfoil-transonic-internal", name="snapshots")
+
+# Load parameters
+ds_params = load_dataset("SISSAmathLab/airfoil-transonic-internal", name="parameters")
+
+# Visualize pressure field in internal domain
+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]
+
+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.xlabel('x')
+plt.ylabel('y')
+plt.axis('equal')
+plt.grid(True, alpha=0.3)
+plt.show()
+```
+
+## Related Datasets
+
+See also: **Airfoil Transonic Boundary** dataset for aerodynamic quantities specifically at the airfoil surface.