---
dataset_info:
- config_name: geometry
  features:
  - name: node_coordinates_x
    list: float64
  - name: node_coordinates_y
    list: float64
  splits:
  - name: default
    num_bytes: 727176
    num_examples: 1
  download_size: 439534
  dataset_size: 727176
- config_name: parameters
  features:
  - name: angle_of_attack
    dtype: float64
  splits:
  - name: default
    num_bytes: 800
    num_examples: 100
  download_size: 1465
  dataset_size: 800
- config_name: snapshots
  features:
  - name: pressure
    list: float64
  - name: velocity
    list: float64
  splits:
  - name: default
    num_bytes: 72717600
    num_examples: 100
  download_size: 49385445
  dataset_size: 72717600
configs:
- config_name: geometry
  data_files:
  - split: default
    path: geometry/default-*
- config_name: parameters
  data_files:
  - split: default
    path: parameters/default-*
- config_name: snapshots
  data_files:
  - 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 angle of attack.

### 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 (angle of attack)

### 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
- `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 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]
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 (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 Boundary** dataset for aerodynamic quantities specifically at the airfoil surface.