README.md

---
dataset_info:
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  - name: node_coordinates_y
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  - name: wall_shear_stress
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configs:
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    path: geometry/default-*
- config_name: parameters
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  - split: default
    path: parameters/default-*
- config_name: snapshots
  data_files:
  - split: default
    path: snapshots/default-*
---
# Airfoil Transonic Flow - Boundary Dataset

## Dataset Description

This dataset contains transonic flow simulations around an airfoil, focusing on boundary (airfoil surface) quantities with varying angle of attack.

### Dataset Summary

The Airfoil Transonic Boundary dataset provides numerical simulations of compressible transonic flow around an airfoil profile. The dataset focuses on aerodynamic quantities at the airfoil surface (boundary), including pressure and wall shear stress distributions, making it valuable for aerodynamic analysis, design optimization, and machine learning applications in aerospace engineering.

## Dataset Structure

### Data Instances

The dataset consists of three configurations:

- **geometry**: Airfoil surface node coordinates
- **snapshots**: Aerodynamic field solutions at the boundary
- **parameters**: Flow condition parameters (angle of attack)

### Data Fields

#### Geometry Configuration
- `node_coordinates_x`: Sequence of x-coordinates of airfoil surface nodes (float64)
- `node_coordinates_y`: Sequence of y-coordinates of airfoil surface nodes (float64)

#### Snapshots Configuration
- `pressure`: Pressure distribution along the airfoil surface (float64)
- `wall_shear_stress`: Wall shear stress distribution along the airfoil surface (float64)

#### Parameters Configuration
- `angle_of_attack`: angle of attack for each simulation (float64)

### Data Splits

- `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 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

Only boundary quantities (at the airfoil surface) are included in this dataset. Solutions are stored as 1D arrays corresponding to the nodes on the airfoil surface.

## 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-boundary", name="geometry")

# Load snapshots
ds_data = load_dataset("SISSAmathLab/airfoil-transonic-boundary", name="snapshots")

# Load parameters
ds_params = load_dataset("SISSAmathLab/airfoil-transonic-boundary", name="parameters")

# Visualize pressure distribution on airfoil surface
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]
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 (angle of attack={angle_of_attack:.2f})')
plt.xlabel('x')
plt.ylabel('y')
plt.axis('equal')
plt.grid(True, alpha=0.3)
plt.show()
```

## Related Datasets

See also: **Airfoil Transonic Internal** dataset for flow field quantities in the internal domain around the airfoil.

## Contact

For questions or issues, please contact SISSA mathLab.